NACA 6-H-15 AIRFOIL (n6h15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 6-H-15 AIRFOIL (n6h15-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.82 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n6h15-il-1000000.txt Download as CSV file: xf-n6h15-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 6-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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3235 0.10922 0.10648 -0.0113 0.6068 0.0156
-11.250 -0.8851 0.03145 0.02733 -0.0204 0.6260 0.0125
-11.000 -0.8847 0.02867 0.02423 -0.0169 0.6237 0.0127
-10.750 -0.8639 0.02851 0.02403 -0.0159 0.6205 0.0129
-10.500 -0.8496 0.02722 0.02260 -0.0141 0.6188 0.0131
-10.250 -0.8225 0.02777 0.02324 -0.0140 0.6166 0.0133
-10.000 -0.8043 0.02689 0.02225 -0.0127 0.6144 0.0135
-9.750 -0.7869 0.02579 0.02099 -0.0113 0.6122 0.0139
-9.500 -0.7713 0.02420 0.01915 -0.0095 0.6100 0.0143
-9.250 -0.7536 0.02280 0.01751 -0.0081 0.6078 0.0147
-9.000 -0.7329 0.02181 0.01630 -0.0070 0.6051 0.0151
-8.750 -0.7137 0.02024 0.01448 -0.0057 0.6036 0.0155
-8.500 -0.6917 0.01937 0.01352 -0.0049 0.6017 0.0160
-8.250 -0.6672 0.01920 0.01333 -0.0044 0.5996 0.0163
-8.000 -0.6423 0.01904 0.01315 -0.0040 0.5975 0.0167
-7.750 -0.6176 0.01877 0.01281 -0.0035 0.5953 0.0172
-7.500 -0.5927 0.01844 0.01240 -0.0030 0.5931 0.0178
-7.250 -0.5676 0.01793 0.01175 -0.0026 0.5906 0.0184
-7.000 -0.5420 0.01767 0.01137 -0.0022 0.5887 0.0188
-6.750 -0.5165 0.01633 0.00990 -0.0020 0.5872 0.0196
-6.500 -0.4907 0.01615 0.00973 -0.0017 0.5854 0.0201
-6.250 -0.4646 0.01591 0.00946 -0.0015 0.5836 0.0207
-6.000 -0.4380 0.01556 0.00905 -0.0013 0.5818 0.0214
-5.750 -0.4111 0.01518 0.00859 -0.0012 0.5800 0.0221
-5.500 -0.3846 0.01510 0.00844 -0.0009 0.5781 0.0228
-5.250 -0.3562 0.01416 0.00740 -0.0012 0.5762 0.0238
-5.000 -0.3291 0.01383 0.00705 -0.0012 0.5741 0.0245
-4.750 -0.3018 0.01358 0.00680 -0.0012 0.5729 0.0253
-4.500 -0.2742 0.01327 0.00646 -0.0012 0.5715 0.0262
-4.250 -0.2467 0.01303 0.00619 -0.0012 0.5698 0.0271
-4.000 -0.2193 0.01289 0.00601 -0.0012 0.5680 0.0278
-3.750 -0.1914 0.01217 0.00526 -0.0013 0.5662 0.0287
-3.500 -0.1648 0.01172 0.00480 -0.0012 0.5644 0.0297
-3.250 -0.1381 0.01148 0.00456 -0.0011 0.5628 0.0306
-3.000 -0.1114 0.01130 0.00435 -0.0009 0.5610 0.0317
-2.750 -0.0850 0.01112 0.00413 -0.0007 0.5590 0.0327
-2.500 -0.0583 0.01090 0.00391 -0.0006 0.5579 0.0334
-2.250 -0.0315 0.01074 0.00375 -0.0004 0.5565 0.0339
-2.000 -0.0069 0.01035 0.00334 0.0001 0.5551 0.0356
-1.750 0.0191 0.01014 0.00314 0.0004 0.5536 0.0369
-1.500 0.0454 0.00999 0.00299 0.0006 0.5522 0.0383
-1.250 0.0718 0.00986 0.00285 0.0008 0.5509 0.0397
-1.000 0.0983 0.00976 0.00273 0.0010 0.5495 0.0410
-0.750 0.1243 0.00962 0.00259 0.0013 0.5481 0.0442
-0.500 0.1504 0.00952 0.00250 0.0015 0.5466 0.0486
-0.250 0.1754 0.00939 0.00245 0.0020 0.5449 0.0726
0.000 0.1989 0.00918 0.00244 0.0027 0.5436 0.1365
0.250 0.2147 0.00859 0.00237 0.0048 0.5428 0.3056
0.500 0.2005 0.00711 0.00208 0.0130 0.5419 0.6740
0.750 0.2056 0.00671 0.00229 0.0182 0.5410 0.8529
1.000 0.2319 0.00687 0.00245 0.0186 0.5398 0.8696
1.250 0.2594 0.00703 0.00263 0.0188 0.5385 0.8803
1.500 0.2869 0.00722 0.00283 0.0190 0.5372 0.8890
1.750 0.3157 0.00734 0.00295 0.0188 0.5360 0.8947
2.000 0.3457 0.00755 0.00318 0.0184 0.5349 0.9009
2.250 0.3724 0.00778 0.00339 0.0187 0.5337 0.9066
2.500 0.4028 0.00785 0.00347 0.0182 0.5325 0.9109
2.750 0.4336 0.00808 0.00369 0.0176 0.5308 0.9148
3.000 0.4615 0.00816 0.00375 0.0174 0.5286 0.9163
3.250 0.4893 0.00816 0.00377 0.0172 0.5269 0.9178
3.500 0.5170 0.00819 0.00381 0.0170 0.5256 0.9191
3.750 0.5445 0.00820 0.00382 0.0168 0.5227 0.9207
4.000 0.5720 0.00816 0.00378 0.0166 0.5194 0.9213
4.250 0.5993 0.00815 0.00375 0.0164 0.5168 0.9215
4.500 0.6265 0.00819 0.00376 0.0162 0.5139 0.9216
4.750 0.6542 0.00815 0.00376 0.0159 0.5117 0.9218
5.000 0.6819 0.00814 0.00378 0.0155 0.5093 0.9220
5.250 0.7095 0.00812 0.00377 0.0152 0.5061 0.9222
5.500 0.7368 0.00813 0.00378 0.0150 0.5028 0.9224
5.750 0.7638 0.00818 0.00382 0.0147 0.4991 0.9226
6.000 0.7913 0.00814 0.00383 0.0144 0.4949 0.9229
6.250 0.8181 0.00811 0.00382 0.0142 0.4892 0.9236
6.500 0.8445 0.00814 0.00386 0.0141 0.4834 0.9243
6.750 0.8717 0.00816 0.00391 0.0138 0.4762 0.9248
7.000 0.8975 0.00823 0.00398 0.0137 0.4662 0.9253
7.250 0.9214 0.00839 0.00410 0.0139 0.4452 0.9259
7.500 0.9240 0.00942 0.00478 0.0173 0.3675 0.9277
7.750 0.9185 0.01054 0.00568 0.0220 0.3240 0.9300
8.000 0.9135 0.01122 0.00632 0.0270 0.3044 0.9326
8.250 0.8958 0.01253 0.00759 0.0330 0.2832 0.9365
8.500 0.8655 0.01514 0.01000 0.0390 0.2315 0.9420
8.750 0.8403 0.01806 0.01278 0.0433 0.1934 0.9482
9.000 0.8281 0.02035 0.01495 0.0462 0.1608 0.9536
9.250 0.8167 0.02410 0.01838 0.0457 0.0914 0.9595
9.500 0.8310 0.02593 0.02016 0.0441 0.0762 0.9621
9.750 0.8503 0.02735 0.02158 0.0424 0.0700 0.9643
10.000 0.8730 0.02847 0.02275 0.0407 0.0682 0.9662
10.250 0.8948 0.02972 0.02402 0.0389 0.0663 0.9680
10.500 0.9156 0.03111 0.02543 0.0370 0.0633 0.9696
10.750 0.9358 0.03264 0.02697 0.0350 0.0605 0.9711
11.000 0.9536 0.03429 0.02867 0.0333 0.0582 0.9728
11.250 0.9753 0.03548 0.02991 0.0317 0.0578 0.9746
11.500 0.9958 0.03674 0.03123 0.0302 0.0569 0.9768
11.750 1.0158 0.03797 0.03249 0.0289 0.0555 0.9792
12.000 1.0339 0.03929 0.03384 0.0278 0.0544 0.9821
12.250 1.0523 0.04068 0.03526 0.0265 0.0527 0.9845
12.500 1.0681 0.04230 0.03690 0.0253 0.0513 0.9875
12.750 1.0810 0.04410 0.03872 0.0244 0.0491 0.9911
13.000 1.0948 0.04598 0.04066 0.0235 0.0479 0.9991
13.250 1.1164 0.04721 0.04192 0.0220 0.0472 0.9998
13.500 1.1282 0.04828 0.04302 0.0224 0.0463 1.0000
13.750 1.1394 0.04928 0.04405 0.0231 0.0450 1.0000
14.000 1.1499 0.05047 0.04525 0.0236 0.0435 1.0000
14.250 1.1591 0.05185 0.04662 0.0240 0.0417 1.0000
14.500 1.1655 0.05353 0.04830 0.0246 0.0394 1.0000
14.750 1.1807 0.05441 0.04922 0.0247 0.0378 1.0000
15.000 1.1924 0.05563 0.05043 0.0249 0.0343 1.0000
15.250 1.2005 0.05725 0.05203 0.0251 0.0301 1.0000
15.500 1.2033 0.05935 0.05402 0.0255 0.0215 1.0000
15.750 1.2066 0.06144 0.05610 0.0259 0.0183 1.0000
16.000 1.2102 0.06358 0.05827 0.0262 0.0167 1.0000
16.250 1.2140 0.06571 0.06043 0.0264 0.0155 1.0000
16.500 1.2159 0.06806 0.06280 0.0266 0.0140 1.0000
16.750 1.2214 0.07012 0.06492 0.0266 0.0137 1.0000
17.000 1.2262 0.07222 0.06707 0.0267 0.0131 1.0000
17.250 1.2316 0.07428 0.06919 0.0267 0.0128 1.0000
17.500 1.2335 0.07677 0.07172 0.0266 0.0121 1.0000
17.750 1.2350 0.07934 0.07435 0.0265 0.0118 1.0000
18.000 1.2341 0.08224 0.07731 0.0264 0.0111 1.0000
18.250 1.2373 0.08468 0.07981 0.0261 0.0109 1.0000
18.500 1.2415 0.08700 0.08221 0.0259 0.0104 1.0000
18.750 1.2449 0.08949 0.08476 0.0255 0.0102 1.0000
19.000 1.2467 0.09219 0.08753 0.0251 0.0100 1.0000
19.250 1.2485 0.09492 0.09031 0.0246 0.0097 1.0000
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