NACA 5-H-15 AIRFOIL (n5h15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 5-H-15 AIRFOIL (n5h15-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.49 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n5h15-il-1000000-n5.txt Download as CSV file: xf-n5h15-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 5-H-15 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -1.1786 0.05079 0.04763 -0.0616 0.7621 0.0133
-17.500 -1.1946 0.04660 0.04329 -0.0624 0.7593 0.0136
-17.250 -1.2077 0.04314 0.03967 -0.0621 0.7563 0.0138
-17.000 -1.2173 0.04030 0.03668 -0.0612 0.7532 0.0139
-16.750 -1.2240 0.03787 0.03407 -0.0598 0.7502 0.0142
-16.500 -1.2196 0.03644 0.03258 -0.0586 0.7471 0.0145
-16.250 -1.2073 0.03569 0.03182 -0.0576 0.7436 0.0148
-16.000 -1.1990 0.03467 0.03073 -0.0563 0.7399 0.0151
-15.750 -1.1872 0.03397 0.02998 -0.0552 0.7366 0.0154
-15.500 -1.1736 0.03340 0.02938 -0.0541 0.7337 0.0158
-15.250 -1.1656 0.03240 0.02830 -0.0525 0.7306 0.0161
-15.000 -1.1549 0.03162 0.02745 -0.0510 0.7272 0.0165
-14.750 -1.1465 0.03066 0.02638 -0.0492 0.7238 0.0168
-14.500 -1.1377 0.02972 0.02533 -0.0473 0.7206 0.0172
-14.250 -1.1295 0.02871 0.02420 -0.0453 0.7177 0.0174
-14.000 -1.1210 0.02771 0.02309 -0.0432 0.7145 0.0176
-13.750 -1.1095 0.02692 0.02218 -0.0414 0.7107 0.0178
-13.500 -1.0967 0.02623 0.02139 -0.0396 0.7072 0.0180
-13.250 -1.0850 0.02557 0.02064 -0.0376 0.7038 0.0183
-13.000 -1.0736 0.02478 0.01977 -0.0355 0.7007 0.0185
-12.750 -1.0578 0.02447 0.01943 -0.0339 0.6973 0.0187
-12.500 -1.0396 0.02447 0.01942 -0.0324 0.6939 0.0190
-12.250 -1.0239 0.02416 0.01907 -0.0307 0.6908 0.0192
-12.000 -1.0083 0.02382 0.01867 -0.0289 0.6879 0.0194
-11.750 -0.9918 0.02360 0.01843 -0.0272 0.6850 0.0196
-11.500 -0.9753 0.02345 0.01824 -0.0254 0.6819 0.0199
-11.250 -0.9603 0.02289 0.01758 -0.0234 0.6789 0.0201
-11.000 -0.9429 0.02254 0.01716 -0.0218 0.6759 0.0204
-10.750 -0.9243 0.02204 0.01657 -0.0205 0.6731 0.0207
-10.500 -0.9043 0.02169 0.01616 -0.0194 0.6705 0.0211
-10.250 -0.8839 0.02130 0.01569 -0.0183 0.6672 0.0215
-10.000 -0.8637 0.02069 0.01498 -0.0172 0.6637 0.0218
-9.750 -0.8427 0.02020 0.01438 -0.0163 0.6601 0.0220
-9.500 -0.8210 0.01984 0.01394 -0.0154 0.6568 0.0222
-9.250 -0.7989 0.01940 0.01343 -0.0146 0.6543 0.0224
-9.000 -0.7765 0.01889 0.01283 -0.0138 0.6514 0.0225
-8.750 -0.7537 0.01843 0.01229 -0.0131 0.6485 0.0226
-8.500 -0.7311 0.01751 0.01124 -0.0125 0.6456 0.0229
-8.000 -0.6848 0.01607 0.00965 -0.0114 0.6400 0.0236
-7.750 -0.6609 0.01559 0.00912 -0.0109 0.6377 0.0238
-7.500 -0.6367 0.01517 0.00865 -0.0104 0.6352 0.0240
-7.250 -0.6124 0.01477 0.00820 -0.0099 0.6326 0.0242
-7.000 -0.5879 0.01439 0.00777 -0.0094 0.6301 0.0244
-6.750 -0.5634 0.01405 0.00738 -0.0090 0.6275 0.0246
-6.500 -0.5387 0.01369 0.00699 -0.0085 0.6252 0.0248
-6.250 -0.5138 0.01334 0.00661 -0.0081 0.6227 0.0250
-6.000 -0.4890 0.01303 0.00626 -0.0077 0.6202 0.0253
-5.750 -0.4641 0.01272 0.00592 -0.0072 0.6175 0.0256
-5.500 -0.4392 0.01243 0.00559 -0.0068 0.6146 0.0259
-5.250 -0.4141 0.01220 0.00531 -0.0064 0.6116 0.0263
-5.000 -0.3888 0.01194 0.00503 -0.0060 0.6093 0.0268
-4.750 -0.3637 0.01167 0.00474 -0.0056 0.6067 0.0270
-4.500 -0.3383 0.01144 0.00448 -0.0052 0.6037 0.0273
-4.250 -0.3131 0.01121 0.00422 -0.0048 0.6008 0.0276
-4.000 -0.2876 0.01101 0.00398 -0.0045 0.5983 0.0278
-3.750 -0.2620 0.01084 0.00378 -0.0042 0.5959 0.0280
-3.500 -0.2362 0.01065 0.00358 -0.0039 0.5938 0.0282
-3.250 -0.2102 0.01047 0.00339 -0.0036 0.5913 0.0283
-3.000 -0.1844 0.01028 0.00319 -0.0033 0.5886 0.0286
-2.750 -0.1592 0.01006 0.00294 -0.0029 0.5857 0.0291
-2.500 -0.1335 0.00989 0.00274 -0.0026 0.5829 0.0298
-2.250 -0.1075 0.00975 0.00259 -0.0023 0.5801 0.0305
-2.000 -0.0811 0.00961 0.00246 -0.0021 0.5772 0.0311
-1.750 -0.0547 0.00949 0.00234 -0.0019 0.5737 0.0319
-1.500 -0.0283 0.00939 0.00224 -0.0018 0.5697 0.0330
-1.250 -0.0019 0.00932 0.00214 -0.0016 0.5657 0.0342
-1.000 0.0250 0.00923 0.00206 -0.0015 0.5621 0.0354
-0.750 0.0516 0.00914 0.00198 -0.0014 0.5574 0.0374
-0.500 0.0779 0.00906 0.00191 -0.0012 0.5525 0.0412
-0.250 0.1045 0.00898 0.00186 -0.0011 0.5480 0.0473
0.000 0.1308 0.00889 0.00181 -0.0009 0.5421 0.0588
0.250 0.1565 0.00881 0.00176 -0.0007 0.5358 0.0783
0.500 0.1801 0.00856 0.00171 0.0000 0.5289 0.1485
0.750 0.1996 0.00816 0.00164 0.0013 0.5209 0.2725
1.000 0.2010 0.00699 0.00146 0.0062 0.5130 0.5724
1.250 0.1956 0.00608 0.00146 0.0134 0.5048 0.8301
1.500 0.2210 0.00617 0.00154 0.0138 0.4936 0.8498
1.750 0.2463 0.00629 0.00164 0.0143 0.4832 0.8655
2.000 0.2727 0.00642 0.00175 0.0145 0.4741 0.8754
2.250 0.2989 0.00654 0.00185 0.0147 0.4660 0.8840
2.500 0.3247 0.00669 0.00198 0.0151 0.4597 0.8926
2.750 0.3506 0.00678 0.00205 0.0153 0.4544 0.8959
3.000 0.3786 0.00686 0.00211 0.0150 0.4494 0.8976
3.250 0.4064 0.00695 0.00220 0.0148 0.4453 0.8999
3.500 0.4342 0.00703 0.00227 0.0146 0.4422 0.9019
3.750 0.4616 0.00710 0.00235 0.0145 0.4391 0.9037
4.000 0.4887 0.00719 0.00243 0.0144 0.4355 0.9051
4.500 0.5415 0.00741 0.00262 0.0144 0.4254 0.9087
4.750 0.5669 0.00755 0.00273 0.0146 0.4178 0.9101
5.000 0.5926 0.00767 0.00284 0.0147 0.4122 0.9113
5.250 0.6187 0.00778 0.00294 0.0147 0.4058 0.9124
5.500 0.6450 0.00791 0.00306 0.0146 0.4005 0.9137
5.750 0.6714 0.00802 0.00319 0.0146 0.3931 0.9151
6.000 0.6959 0.00822 0.00335 0.0148 0.3811 0.9166
6.250 0.7198 0.00842 0.00352 0.0151 0.3673 0.9181
6.500 0.7361 0.00891 0.00383 0.0167 0.3192 0.9204
6.750 0.7249 0.01028 0.00477 0.0227 0.2299 0.9256
7.000 0.7197 0.01110 0.00542 0.0279 0.1879 0.9306
7.250 0.7136 0.01219 0.00639 0.0324 0.1519 0.9381
7.500 0.7065 0.01378 0.00777 0.0361 0.1003 0.9465
7.750 0.7144 0.01542 0.00923 0.0365 0.0542 0.9534
8.250 0.7545 0.01781 0.01149 0.0341 0.0150 0.9618
8.500 0.7826 0.01855 0.01225 0.0322 0.0142 0.9640
8.750 0.8092 0.01944 0.01316 0.0303 0.0126 0.9661
9.000 0.8338 0.02041 0.01417 0.0286 0.0114 0.9686
9.250 0.8572 0.02128 0.01506 0.0274 0.0109 0.9716
9.500 0.8808 0.02222 0.01603 0.0260 0.0104 0.9737
9.750 0.9032 0.02320 0.01704 0.0247 0.0098 0.9760
10.000 0.9233 0.02428 0.01814 0.0238 0.0094 0.9789
10.250 0.9411 0.02538 0.01928 0.0232 0.0091 0.9827
10.500 0.9571 0.02674 0.02067 0.0226 0.0085 0.9859
10.750 0.9750 0.02789 0.02185 0.0219 0.0081 0.9892
11.000 0.9911 0.02910 0.02310 0.0215 0.0079 0.9927
11.250 1.0059 0.03047 0.02450 0.0213 0.0078 0.9983
11.500 1.0231 0.03190 0.02597 0.0204 0.0075 0.9994
11.750 1.0407 0.03305 0.02713 0.0198 0.0070 1.0000
12.000 1.0433 0.03452 0.02866 0.0215 0.0072 1.0000
12.250 1.0501 0.03578 0.02994 0.0228 0.0069 1.0000
12.500 1.0576 0.03708 0.03126 0.0239 0.0066 1.0000
12.750 1.0647 0.03847 0.03268 0.0249 0.0064 1.0000
13.000 1.0698 0.04012 0.03438 0.0259 0.0064 1.0000
13.250 1.0757 0.04173 0.03603 0.0268 0.0063 1.0000
13.500 1.0775 0.04378 0.03813 0.0277 0.0060 1.0000
13.750 1.0832 0.04553 0.03993 0.0284 0.0060 1.0000
14.000 1.0896 0.04728 0.04173 0.0289 0.0059 1.0000
14.250 1.1007 0.04858 0.04306 0.0292 0.0057 1.0000
14.500 1.1054 0.05055 0.04508 0.0297 0.0056 1.0000
14.750 1.1114 0.05242 0.04701 0.0301 0.0055 1.0000
15.000 1.1150 0.05459 0.04924 0.0304 0.0055 1.0000
15.250 1.1211 0.05651 0.05120 0.0307 0.0054 1.0000
15.500 1.1261 0.05860 0.05336 0.0308 0.0053 1.0000
15.750 1.1321 0.06059 0.05539 0.0309 0.0052 1.0000
16.000 1.1394 0.06250 0.05734 0.0309 0.0050 1.0000
16.250 1.1446 0.06465 0.05954 0.0309 0.0049 1.0000
16.500 1.1474 0.06712 0.06208 0.0309 0.0049 1.0000
16.750 1.1527 0.06931 0.06431 0.0308 0.0048 1.0000
17.000 1.1566 0.07170 0.06676 0.0305 0.0047 1.0000
17.250 1.1616 0.07398 0.06908 0.0303 0.0046 1.0000
17.500 1.1627 0.07678 0.07195 0.0300 0.0046 1.0000
17.750 1.1648 0.07948 0.07470 0.0296 0.0044 1.0000
18.000 1.1658 0.08234 0.07763 0.0292 0.0045 1.0000
18.250 1.1652 0.08543 0.08079 0.0287 0.0044 1.0000
18.500 1.1643 0.08860 0.08403 0.0281 0.0043 1.0000
18.750 1.1583 0.09247 0.08798 0.0274 0.0042 1.0000
19.000 1.1574 0.09573 0.09131 0.0266 0.0042 1.0000
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