NACA 5-H-15 AIRFOIL (n5h15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 5-H-15 AIRFOIL (n5h15-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.79 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n5h15-il-1000000.txt Download as CSV file: xf-n5h15-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4262 0.09741 0.09477 -0.0352 0.7065 0.0231
-11.250 -0.8144 0.03883 0.03511 -0.0417 0.7117 0.0211
-11.000 -0.8449 0.03532 0.03132 -0.0343 0.7088 0.0213
-10.750 -0.8311 0.03514 0.03115 -0.0325 0.7057 0.0216
-10.500 -0.8268 0.03366 0.02952 -0.0296 0.7028 0.0218
-10.250 -0.8076 0.03387 0.02972 -0.0285 0.6995 0.0220
-10.000 -0.7821 0.03480 0.03073 -0.0283 0.6961 0.0222
-9.750 -0.7547 0.03599 0.03202 -0.0284 0.6925 0.0224
-9.500 -0.7397 0.03545 0.03141 -0.0269 0.6892 0.0227
-9.250 -0.7389 0.03255 0.02823 -0.0233 0.6864 0.0231
-9.000 -0.7339 0.02991 0.02529 -0.0202 0.6836 0.0236
-8.750 -0.7235 0.02774 0.02285 -0.0177 0.6810 0.0243
-8.500 -0.7092 0.02603 0.02090 -0.0156 0.6785 0.0249
-8.250 -0.6914 0.02486 0.01954 -0.0141 0.6757 0.0253
-8.000 -0.6708 0.02442 0.01895 -0.0129 0.6731 0.0256
-7.750 -0.6578 0.02103 0.01516 -0.0109 0.6707 0.0262
-7.500 -0.6355 0.01997 0.01400 -0.0104 0.6678 0.0267
-7.250 -0.6119 0.01931 0.01329 -0.0098 0.6654 0.0271
-7.000 -0.5875 0.01857 0.01248 -0.0094 0.6628 0.0274
-6.750 -0.5627 0.01790 0.01173 -0.0090 0.6602 0.0277
-6.500 -0.5372 0.01725 0.01102 -0.0088 0.6577 0.0281
-6.250 -0.5114 0.01661 0.01029 -0.0085 0.6554 0.0285
-6.000 -0.4853 0.01602 0.00962 -0.0084 0.6528 0.0290
-5.750 -0.4588 0.01545 0.00899 -0.0083 0.6505 0.0295
-5.500 -0.4321 0.01495 0.00845 -0.0082 0.6480 0.0299
-5.250 -0.4052 0.01441 0.00787 -0.0081 0.6453 0.0303
-5.000 -0.3784 0.01390 0.00730 -0.0080 0.6425 0.0306
-4.750 -0.3519 0.01349 0.00683 -0.0079 0.6397 0.0309
-4.500 -0.3257 0.01312 0.00641 -0.0077 0.6368 0.0311
-4.250 -0.2992 0.01278 0.00605 -0.0075 0.6348 0.0313
-4.000 -0.2742 0.01211 0.00535 -0.0071 0.6327 0.0317
-3.750 -0.2513 0.01142 0.00465 -0.0063 0.6304 0.0326
-3.500 -0.2268 0.01108 0.00429 -0.0058 0.6281 0.0332
-3.250 -0.2015 0.01084 0.00405 -0.0054 0.6256 0.0341
-3.000 -0.1762 0.01063 0.00381 -0.0050 0.6231 0.0348
-2.750 -0.1509 0.01043 0.00358 -0.0046 0.6206 0.0355
-2.500 -0.1252 0.01022 0.00337 -0.0042 0.6184 0.0363
-2.250 -0.0993 0.01003 0.00317 -0.0039 0.6159 0.0370
-2.000 -0.0732 0.00986 0.00300 -0.0036 0.6133 0.0378
-1.750 -0.0470 0.00973 0.00285 -0.0034 0.6106 0.0384
-1.500 -0.0223 0.00949 0.00256 -0.0028 0.6078 0.0407
-1.250 0.0037 0.00935 0.00243 -0.0026 0.6050 0.0429
-1.000 0.0303 0.00923 0.00233 -0.0024 0.6024 0.0457
-0.750 0.0566 0.00908 0.00221 -0.0022 0.5994 0.0510
-0.500 0.0822 0.00891 0.00209 -0.0018 0.5962 0.0658
-0.250 0.0989 0.00824 0.00193 0.0001 0.5930 0.2320
0.000 0.1095 0.00739 0.00178 0.0032 0.5898 0.4433
0.250 0.0933 0.00586 0.00158 0.0123 0.5870 0.7933
0.500 0.1156 0.00586 0.00173 0.0137 0.5832 0.8552
0.750 0.1410 0.00594 0.00181 0.0144 0.5790 0.8728
1.000 0.1683 0.00606 0.00193 0.0146 0.5748 0.8849
1.250 0.1956 0.00614 0.00203 0.0148 0.5705 0.8944
1.500 0.2241 0.00626 0.00215 0.0148 0.5655 0.9015
1.750 0.2497 0.00637 0.00221 0.0152 0.5603 0.9076
2.000 0.2820 0.00658 0.00247 0.0145 0.5547 0.9160
2.250 0.3063 0.00674 0.00261 0.0154 0.5482 0.9228
2.500 0.3363 0.00677 0.00262 0.0148 0.5413 0.9250
2.750 0.3663 0.00685 0.00268 0.0142 0.5327 0.9268
3.000 0.3958 0.00694 0.00274 0.0137 0.5239 0.9286
3.250 0.4235 0.00703 0.00279 0.0135 0.5141 0.9303
3.500 0.4502 0.00712 0.00285 0.0135 0.5038 0.9322
3.750 0.4759 0.00720 0.00290 0.0137 0.4948 0.9343
4.000 0.5000 0.00731 0.00296 0.0142 0.4861 0.9363
4.250 0.5244 0.00738 0.00301 0.0146 0.4785 0.9379
4.500 0.5495 0.00747 0.00306 0.0148 0.4710 0.9394
4.750 0.5773 0.00753 0.00312 0.0145 0.4647 0.9405
5.000 0.6036 0.00768 0.00323 0.0145 0.4553 0.9416
5.250 0.6310 0.00777 0.00332 0.0142 0.4482 0.9427
5.500 0.6569 0.00794 0.00345 0.0142 0.4412 0.9440
5.750 0.6843 0.00801 0.00355 0.0139 0.4362 0.9452
6.000 0.7097 0.00816 0.00369 0.0140 0.4290 0.9469
6.250 0.7347 0.00828 0.00381 0.0142 0.4217 0.9487
6.500 0.7581 0.00841 0.00394 0.0147 0.4139 0.9507
6.750 0.7804 0.00853 0.00406 0.0155 0.4056 0.9527
7.000 0.8012 0.00872 0.00421 0.0164 0.3937 0.9548
7.250 0.8268 0.00891 0.00438 0.0163 0.3797 0.9564
7.500 0.8475 0.00935 0.00469 0.0168 0.3384 0.9586
7.750 0.8265 0.01112 0.00595 0.0239 0.2332 0.9683
8.000 0.8330 0.01334 0.00779 0.0234 0.1555 0.9732
8.250 0.8346 0.01643 0.01042 0.0222 0.0646 0.9778
8.500 0.8468 0.01770 0.01161 0.0225 0.0453 0.9821
8.750 0.8619 0.01949 0.01326 0.0212 0.0195 0.9839
9.000 0.8832 0.02065 0.01444 0.0200 0.0169 0.9854
9.250 0.9055 0.02161 0.01544 0.0188 0.0159 0.9870
9.500 0.9254 0.02273 0.01660 0.0179 0.0151 0.9891
9.750 0.9417 0.02409 0.01800 0.0172 0.0142 0.9917
10.000 0.9566 0.02555 0.01952 0.0167 0.0136 0.9943
10.250 0.9746 0.02699 0.02100 0.0155 0.0131 0.9963
10.500 0.9935 0.02832 0.02238 0.0143 0.0130 0.9980
10.750 1.0121 0.02970 0.02379 0.0132 0.0125 0.9992
11.000 1.0242 0.03112 0.02526 0.0131 0.0120 1.0000
11.250 1.0153 0.03223 0.02641 0.0174 0.0120 1.0000
11.500 1.0160 0.03351 0.02771 0.0198 0.0116 1.0000
11.750 1.0182 0.03498 0.02922 0.0216 0.0114 1.0000
12.000 1.0190 0.03669 0.03096 0.0233 0.0110 1.0000
12.250 1.0247 0.03814 0.03245 0.0245 0.0111 1.0000
12.500 1.0208 0.04047 0.03482 0.0261 0.0105 1.0000
12.750 1.0146 0.04307 0.03748 0.0277 0.0104 1.0000
13.000 1.0279 0.04412 0.03857 0.0281 0.0101 1.0000
13.250 1.0329 0.04591 0.04040 0.0289 0.0101 1.0000
13.500 1.0371 0.04779 0.04233 0.0297 0.0101 1.0000
13.750 1.0460 0.04934 0.04392 0.0301 0.0095 1.0000
14.000 1.0512 0.05118 0.04581 0.0307 0.0096 1.0000
14.250 1.0576 0.05299 0.04767 0.0312 0.0094 1.0000
14.500 1.0633 0.05487 0.04959 0.0317 0.0092 1.0000
14.750 1.0686 0.05679 0.05155 0.0321 0.0092 1.0000
15.000 1.0765 0.05858 0.05338 0.0323 0.0089 1.0000
15.250 1.0818 0.06050 0.05534 0.0327 0.0088 1.0000
15.500 1.0888 0.06246 0.05734 0.0327 0.0085 1.0000
15.750 1.0937 0.06446 0.05937 0.0331 0.0084 1.0000
16.000 1.1000 0.06637 0.06132 0.0333 0.0083 1.0000
16.250 1.1058 0.06829 0.06329 0.0336 0.0083 1.0000
16.500 1.1118 0.07001 0.06502 0.0342 0.0081 1.0000
16.750 1.1202 0.07109 0.06614 0.0356 0.0078 1.0000
17.000 1.1284 0.07266 0.06777 0.0362 0.0078 1.0000
17.250 1.1295 0.07578 0.07100 0.0351 0.0077 1.0000
17.500 1.1379 0.07717 0.07244 0.0360 0.0078 1.0000
17.750 1.1410 0.07977 0.07513 0.0356 0.0077 1.0000
18.000 1.1399 0.08329 0.07877 0.0344 0.0075 1.0000
18.250 1.1420 0.08606 0.08163 0.0339 0.0074 1.0000
18.500 1.1432 0.08885 0.08453 0.0337 0.0074 1.0000
18.750 1.1431 0.09212 0.08789 0.0327 0.0072 1.0000
19.000 1.1425 0.09521 0.09108 0.0323 0.0072 1.0000
19.250 1.1401 0.09889 0.09487 0.0311 0.0070 1.0000
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