NACA 6-H-15 AIRFOIL (n6h15-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 6-H-15 AIRFOIL (n6h15-il) Reynolds number: 200,000 Max Cl/Cd: 53.11 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n6h15-il-200000-n5.txt Download as CSV file: xf-n6h15-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3483 0.09255 0.08792 -0.0308 0.6370 0.0193
-9.750 -0.3528 0.08801 0.08342 -0.0336 0.6351 0.0193
-9.500 -0.3593 0.08348 0.07892 -0.0369 0.6333 0.0198
-9.250 -0.3723 0.07849 0.07393 -0.0398 0.6315 0.0198
-9.000 -0.3901 0.07357 0.06898 -0.0410 0.6299 0.0194
-8.750 -0.4042 0.06977 0.06512 -0.0402 0.6282 0.0195
-8.500 -0.4165 0.06656 0.06181 -0.0383 0.6267 0.0200
-8.250 -0.4260 0.06250 0.05761 -0.0367 0.6254 0.0200
-8.000 -0.4326 0.05834 0.05325 -0.0346 0.6241 0.0202
-7.750 -0.4368 0.05393 0.04864 -0.0323 0.6226 0.0204
-7.500 -0.4395 0.04912 0.04356 -0.0295 0.6208 0.0207
-7.250 -0.4610 0.03824 0.03175 -0.0227 0.6197 0.0222
-7.000 -0.4469 0.03658 0.02992 -0.0212 0.6176 0.0229
-6.750 -0.4265 0.03623 0.02953 -0.0206 0.6155 0.0236
-6.500 -0.4113 0.03406 0.02707 -0.0188 0.6138 0.0244
-6.250 -0.3966 0.03102 0.02354 -0.0166 0.6123 0.0255
-6.000 -0.3786 0.02812 0.01990 -0.0145 0.6108 0.0275
-5.750 -0.3563 0.02684 0.01845 -0.0138 0.6094 0.0287
-5.500 -0.3323 0.02593 0.01739 -0.0134 0.6079 0.0298
-5.250 -0.3065 0.02485 0.01614 -0.0131 0.6056 0.0309
-5.000 -0.2798 0.02391 0.01497 -0.0130 0.6034 0.0328
-4.750 -0.2523 0.02308 0.01385 -0.0129 0.6014 0.0343
-4.500 -0.2224 0.02181 0.01247 -0.0134 0.5996 0.0356
-4.250 -0.1942 0.02114 0.01175 -0.0137 0.5980 0.0371
-4.000 -0.1659 0.02058 0.01111 -0.0140 0.5965 0.0389
-3.750 -0.1366 0.01995 0.01038 -0.0143 0.5952 0.0404
-3.500 -0.1074 0.01936 0.00968 -0.0146 0.5940 0.0416
-3.250 -0.0792 0.01896 0.00916 -0.0148 0.5929 0.0430
-3.000 -0.0511 0.01834 0.00860 -0.0151 0.5911 0.0450
-2.750 -0.0244 0.01797 0.00826 -0.0151 0.5894 0.0465
-2.500 0.0016 0.01767 0.00796 -0.0150 0.5877 0.0481
-2.250 0.0270 0.01742 0.00770 -0.0147 0.5861 0.0499
-2.000 0.0523 0.01722 0.00747 -0.0144 0.5846 0.0524
-1.750 0.0768 0.01698 0.00722 -0.0139 0.5831 0.0557
-1.500 0.1013 0.01678 0.00702 -0.0134 0.5817 0.0600
-1.250 0.1259 0.01661 0.00683 -0.0129 0.5804 0.0663
-1.000 0.1497 0.01641 0.00670 -0.0123 0.5793 0.0841
-0.750 0.1734 0.01623 0.00660 -0.0117 0.5783 0.1210
-0.500 0.1949 0.01593 0.00652 -0.0107 0.5773 0.1877
-0.250 0.1817 0.01430 0.00650 -0.0032 0.5758 0.6033
0.250 0.3139 0.01705 0.00986 -0.0149 0.5723 0.9111
0.750 0.4349 0.01797 0.01062 -0.0274 0.5685 0.9324
1.000 0.4776 0.01812 0.01070 -0.0306 0.5671 0.9379
1.250 0.5044 0.01821 0.01075 -0.0306 0.5658 0.9418
1.500 0.5247 0.01827 0.01077 -0.0294 0.5646 0.9440
1.750 0.5451 0.01831 0.01077 -0.0283 0.5636 0.9450
2.000 0.5694 0.01831 0.01073 -0.0279 0.5627 0.9452
2.250 0.5932 0.01838 0.01080 -0.0276 0.5613 0.9453
2.500 0.6164 0.01858 0.01107 -0.0274 0.5591 0.9455
2.750 0.6396 0.01876 0.01128 -0.0271 0.5571 0.9458
3.000 0.6630 0.01891 0.01147 -0.0268 0.5554 0.9460
3.250 0.6864 0.01906 0.01165 -0.0266 0.5539 0.9463
3.500 0.7097 0.01919 0.01182 -0.0262 0.5526 0.9466
3.750 0.7344 0.01932 0.01197 -0.0262 0.5513 0.9470
4.000 0.7600 0.01934 0.01201 -0.0261 0.5499 0.9475
4.250 0.7858 0.01909 0.01171 -0.0258 0.5478 0.9478
4.500 0.8079 0.01919 0.01188 -0.0252 0.5443 0.9482
4.750 0.8289 0.01931 0.01210 -0.0246 0.5394 0.9488
5.000 0.8521 0.01927 0.01208 -0.0241 0.5364 0.9492
5.250 0.8779 0.01889 0.01167 -0.0237 0.5330 0.9496
5.500 0.9001 0.01891 0.01175 -0.0231 0.5295 0.9502
5.750 0.9187 0.01917 0.01214 -0.0221 0.5246 0.9510
6.000 0.9407 0.01912 0.01214 -0.0214 0.5208 0.9517
6.250 0.9657 0.01879 0.01180 -0.0209 0.5170 0.9523
6.500 0.9815 0.01913 0.01230 -0.0196 0.5111 0.9538
6.750 1.0007 0.01904 0.01226 -0.0184 0.5043 0.9551
7.000 1.0149 0.01911 0.01241 -0.0164 0.4975 0.9565
7.250 1.0214 0.01933 0.01272 -0.0131 0.4906 0.9586
7.500 1.0312 0.01945 0.01291 -0.0104 0.4837 0.9603
7.750 1.0485 0.01981 0.01337 -0.0097 0.4740 0.9615
8.000 1.0583 0.02057 0.01427 -0.0083 0.4637 0.9634
8.250 1.0502 0.02182 0.01561 -0.0048 0.4534 0.9672
8.500 1.0272 0.02378 0.01765 0.0002 0.4426 0.9733
8.750 1.0431 0.02428 0.01802 0.0005 0.4000 0.9748
9.000 1.0399 0.02584 0.01915 0.0024 0.3494 0.9778
9.250 1.0311 0.02812 0.02129 0.0043 0.3275 0.9815
9.500 1.0223 0.03047 0.02353 0.0062 0.3021 0.9850
9.750 1.0083 0.03381 0.02661 0.0072 0.2366 0.9880
10.000 0.9867 0.03777 0.03022 0.0086 0.1950 0.9917
10.250 0.9831 0.04043 0.03275 0.0093 0.1629 0.9945
10.500 0.9733 0.04396 0.03597 0.0096 0.1126 0.9976
10.750 0.9767 0.04650 0.03840 0.0094 0.0962 0.9997
11.000 0.9729 0.04804 0.03993 0.0119 0.0909 1.0000
11.500 0.9647 0.05070 0.04260 0.0176 0.0845 1.0000
11.750 0.9638 0.05220 0.04412 0.0196 0.0823 1.0000
12.000 0.9649 0.05379 0.04572 0.0213 0.0801 1.0000
12.250 0.9696 0.05522 0.04721 0.0225 0.0788 1.0000
12.500 0.9747 0.05673 0.04879 0.0236 0.0775 1.0000
12.750 0.9802 0.05827 0.05040 0.0246 0.0762 1.0000
13.000 0.9862 0.05982 0.05202 0.0255 0.0751 1.0000
13.250 0.9922 0.06142 0.05367 0.0262 0.0735 1.0000
13.500 0.9977 0.06309 0.05538 0.0270 0.0721 1.0000
13.750 1.0031 0.06479 0.05709 0.0276 0.0700 1.0000
14.000 1.0077 0.06651 0.05880 0.0284 0.0677 1.0000
14.250 1.0170 0.06793 0.06030 0.0288 0.0661 1.0000
14.500 1.0258 0.06943 0.06191 0.0292 0.0641 1.0000
14.750 1.0340 0.07101 0.06357 0.0295 0.0617 1.0000
15.000 1.0414 0.07271 0.06532 0.0298 0.0593 1.0000
15.250 1.0478 0.07450 0.06713 0.0300 0.0571 1.0000
15.500 1.0541 0.07620 0.06884 0.0304 0.0548 1.0000
15.750 1.0626 0.07797 0.07076 0.0304 0.0527 1.0000
16.000 1.0711 0.07966 0.07257 0.0305 0.0509 1.0000
16.250 1.0777 0.08167 0.07467 0.0303 0.0481 1.0000
16.500 1.0824 0.08390 0.07695 0.0302 0.0458 1.0000
16.750 1.0890 0.08593 0.07907 0.0300 0.0433 1.0000
17.000 1.0964 0.08791 0.08120 0.0298 0.0398 1.0000
17.250 1.1012 0.09031 0.08366 0.0293 0.0357 1.0000
17.500 1.1078 0.09241 0.08586 0.0290 0.0315 1.0000
17.750 1.1118 0.09486 0.08835 0.0286 0.0269 1.0000
18.000 1.1145 0.09749 0.09100 0.0281 0.0235 1.0000
18.250 1.1160 0.10030 0.09383 0.0276 0.0213 1.0000
18.500 1.1164 0.10326 0.09682 0.0271 0.0199 1.0000
18.750 1.1166 0.10627 0.09990 0.0265 0.0182 1.0000
19.000 1.1150 0.10958 0.10327 0.0257 0.0171 1.0000
19.250 1.1119 0.11319 0.10695 0.0248 0.0164 1.0000
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