RAE 100 AIRFOIL (rae100-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 100 AIRFOIL (rae100-il) Reynolds number: 500,000 Max Cl/Cd: 60.44 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae100-il-500000.txt Download as CSV file: xf-rae100-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 100 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.9325 0.10362 0.10093 0.0020 1.0000 0.0169
-15.000 -0.9808 0.08873 0.08583 -0.0076 1.0000 0.0165
-14.750 -1.0242 0.07608 0.07295 -0.0161 1.0000 0.0160
-14.500 -1.0511 0.06730 0.06397 -0.0221 1.0000 0.0159
-14.250 -1.0710 0.06031 0.05680 -0.0269 1.0000 0.0160
-14.000 -1.0865 0.05451 0.05083 -0.0305 1.0000 0.0160
-13.750 -1.1010 0.04937 0.04549 -0.0333 1.0000 0.0160
-13.500 -1.1099 0.04548 0.04144 -0.0350 1.0000 0.0164
-13.250 -1.1179 0.04208 0.03786 -0.0358 1.0000 0.0164
-13.000 -1.1251 0.03912 0.03473 -0.0356 1.0000 0.0166
-12.750 -1.1302 0.03672 0.03215 -0.0345 1.0000 0.0169
-12.500 -1.1334 0.03468 0.02993 -0.0327 1.0000 0.0170
-12.250 -1.1337 0.03310 0.02818 -0.0302 1.0000 0.0173
-12.000 -1.1319 0.03170 0.02660 -0.0275 1.0000 0.0175
-11.750 -1.1293 0.02953 0.02423 -0.0251 1.0000 0.0178
-11.500 -1.1227 0.02747 0.02205 -0.0231 1.0000 0.0183
-11.250 -1.1098 0.02625 0.02076 -0.0216 1.0000 0.0188
-11.000 -1.0941 0.02531 0.01975 -0.0203 1.0000 0.0193
-10.750 -1.0778 0.02429 0.01864 -0.0190 1.0000 0.0199
-10.500 -1.0602 0.02339 0.01763 -0.0178 1.0000 0.0207
-10.250 -1.0410 0.02264 0.01677 -0.0167 1.0000 0.0215
-10.000 -1.0215 0.02185 0.01586 -0.0156 1.0000 0.0221
-9.750 -1.0075 0.02020 0.01412 -0.0139 1.0000 0.0231
-9.500 -0.9876 0.01943 0.01333 -0.0129 1.0000 0.0241
-9.250 -0.9668 0.01875 0.01260 -0.0119 1.0000 0.0252
-9.000 -0.9455 0.01810 0.01187 -0.0109 1.0000 0.0264
-8.750 -0.9227 0.01763 0.01131 -0.0101 1.0000 0.0273
-8.500 -0.9056 0.01642 0.01007 -0.0086 1.0000 0.0293
-8.250 -0.8833 0.01590 0.00953 -0.0077 1.0000 0.0311
-8.000 -0.8607 0.01540 0.00897 -0.0068 1.0000 0.0329
-7.750 -0.8399 0.01467 0.00817 -0.0056 1.0000 0.0349
-7.500 -0.8182 0.01408 0.00758 -0.0046 1.0000 0.0377
-7.250 -0.7948 0.01370 0.00717 -0.0037 1.0000 0.0406
-7.000 -0.7735 0.01307 0.00652 -0.0025 1.0000 0.0443
-6.750 -0.7506 0.01265 0.00610 -0.0016 1.0000 0.0485
-6.500 -0.7282 0.01217 0.00560 -0.0005 1.0000 0.0537
-6.250 -0.7052 0.01179 0.00523 0.0004 1.0000 0.0600
-6.000 -0.6828 0.01133 0.00482 0.0014 1.0000 0.0686
-5.750 -0.6601 0.01093 0.00446 0.0024 1.0000 0.0790
-5.500 -0.6374 0.01054 0.00413 0.0034 1.0000 0.0927
-5.250 -0.6148 0.01018 0.00384 0.0044 1.0000 0.1097
-5.000 -0.5924 0.00981 0.00357 0.0055 1.0000 0.1305
-4.750 -0.5700 0.00947 0.00333 0.0065 1.0000 0.1543
-4.500 -0.5478 0.00913 0.00311 0.0076 1.0000 0.1810
-4.250 -0.5258 0.00882 0.00293 0.0087 1.0000 0.2096
-4.000 -0.5039 0.00854 0.00277 0.0098 1.0000 0.2396
-3.750 -0.4822 0.00828 0.00264 0.0109 1.0000 0.2705
-3.500 -0.4535 0.00803 0.00252 0.0106 0.9984 0.3053
-3.250 -0.4136 0.00776 0.00242 0.0079 0.9937 0.3463
-3.000 -0.3757 0.00750 0.00230 0.0057 0.9877 0.3850
-2.750 -0.3357 0.00726 0.00221 0.0031 0.9827 0.4243
-2.500 -0.2992 0.00702 0.00211 0.0013 0.9745 0.4601
-2.250 -0.2608 0.00680 0.00202 -0.0009 0.9671 0.4954
-2.000 -0.2237 0.00660 0.00193 -0.0027 0.9564 0.5291
-1.750 -0.1887 0.00641 0.00185 -0.0040 0.9416 0.5614
-1.500 -0.1564 0.00626 0.00177 -0.0046 0.9212 0.5910
-1.250 -0.1270 0.00615 0.00170 -0.0045 0.8964 0.6198
-1.000 -0.1005 0.00608 0.00165 -0.0038 0.8681 0.6471
-0.750 -0.0750 0.00604 0.00161 -0.0029 0.8391 0.6744
-0.500 -0.0500 0.00602 0.00158 -0.0019 0.8103 0.7009
-0.250 -0.0250 0.00601 0.00156 -0.0010 0.7823 0.7275
0.000 0.0000 0.00602 0.00156 0.0000 0.7547 0.7547
0.250 0.0250 0.00601 0.00156 0.0010 0.7275 0.7824
0.500 0.0499 0.00602 0.00158 0.0019 0.7009 0.8103
0.750 0.0749 0.00604 0.00161 0.0029 0.6742 0.8391
1.000 0.1005 0.00608 0.00165 0.0038 0.6471 0.8681
1.250 0.1270 0.00615 0.00170 0.0045 0.6197 0.8964
1.500 0.1564 0.00626 0.00177 0.0046 0.5910 0.9212
1.750 0.1887 0.00641 0.00185 0.0039 0.5613 0.9416
2.000 0.2236 0.00660 0.00193 0.0027 0.5292 0.9563
2.250 0.2608 0.00680 0.00202 0.0009 0.4955 0.9669
2.500 0.2992 0.00703 0.00211 -0.0013 0.4600 0.9744
2.750 0.3357 0.00726 0.00221 -0.0031 0.4240 0.9826
3.000 0.3757 0.00750 0.00231 -0.0057 0.3849 0.9877
3.250 0.4137 0.00776 0.00242 -0.0079 0.3466 0.9936
3.500 0.4534 0.00803 0.00253 -0.0106 0.3054 0.9984
3.750 0.4824 0.00828 0.00264 -0.0110 0.2703 1.0000
4.000 0.5041 0.00854 0.00277 -0.0098 0.2395 1.0000
4.250 0.5261 0.00882 0.00293 -0.0087 0.2096 1.0000
4.500 0.5481 0.00913 0.00312 -0.0076 0.1811 1.0000
4.750 0.5702 0.00947 0.00333 -0.0066 0.1542 1.0000
5.000 0.5926 0.00981 0.00357 -0.0055 0.1303 1.0000
5.250 0.6150 0.01018 0.00384 -0.0045 0.1096 1.0000
5.500 0.6376 0.01055 0.00413 -0.0035 0.0927 1.0000
5.750 0.6603 0.01093 0.00446 -0.0025 0.0790 1.0000
6.000 0.6830 0.01133 0.00482 -0.0015 0.0685 1.0000
6.250 0.7053 0.01180 0.00524 -0.0004 0.0600 1.0000
6.500 0.7284 0.01217 0.00560 0.0005 0.0538 1.0000
6.750 0.7508 0.01265 0.00610 0.0016 0.0484 1.0000
7.000 0.7736 0.01307 0.00652 0.0025 0.0443 1.0000
7.250 0.7948 0.01370 0.00717 0.0037 0.0406 1.0000
7.500 0.8181 0.01409 0.00759 0.0046 0.0377 1.0000
7.750 0.8398 0.01468 0.00818 0.0056 0.0349 1.0000
8.000 0.8605 0.01541 0.00898 0.0068 0.0329 1.0000
8.250 0.8832 0.01590 0.00952 0.0077 0.0311 1.0000
8.500 0.9055 0.01641 0.01006 0.0086 0.0293 1.0000
8.750 0.9229 0.01758 0.01126 0.0100 0.0274 1.0000
9.000 0.9453 0.01809 0.01186 0.0109 0.0264 1.0000
9.250 0.9666 0.01875 0.01260 0.0119 0.0253 1.0000
9.500 0.9875 0.01942 0.01332 0.0129 0.0241 1.0000
9.750 1.0072 0.02020 0.01414 0.0140 0.0232 1.0000
10.000 1.0217 0.02176 0.01577 0.0156 0.0222 1.0000
10.250 1.0408 0.02260 0.01673 0.0167 0.0214 1.0000
10.500 1.0594 0.02345 0.01770 0.0179 0.0208 1.0000
10.750 1.0773 0.02429 0.01864 0.0191 0.0199 1.0000
11.000 1.0939 0.02522 0.01966 0.0204 0.0193 1.0000
11.250 1.1094 0.02620 0.02072 0.0217 0.0188 1.0000
11.500 1.1222 0.02747 0.02206 0.0233 0.0184 1.0000
11.750 1.1280 0.02960 0.02431 0.0253 0.0178 1.0000
12.000 1.1320 0.03147 0.02638 0.0276 0.0174 1.0000
12.250 1.1345 0.03280 0.02787 0.0303 0.0172 1.0000
12.500 1.1334 0.03458 0.02982 0.0327 0.0170 1.0000
12.750 1.1306 0.03657 0.03199 0.0346 0.0168 1.0000
13.000 1.1254 0.03901 0.03461 0.0357 0.0166 1.0000
13.250 1.1184 0.04194 0.03772 0.0358 0.0164 1.0000
13.500 1.1093 0.04549 0.04145 0.0350 0.0163 1.0000
13.750 1.1003 0.04943 0.04555 0.0333 0.0161 1.0000
14.000 1.0902 0.05392 0.05020 0.0308 0.0159 1.0000
14.250 1.0694 0.06054 0.05704 0.0267 0.0160 1.0000
14.500 1.0484 0.06778 0.06447 0.0218 0.0160 1.0000
14.750 1.0188 0.07712 0.07402 0.0154 0.0161 1.0000
15.000 0.9779 0.08940 0.08652 0.0071 0.0165 1.0000
15.250 0.9297 0.10440 0.10172 -0.0026 0.0169 1.0000
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