NACA 1-H-15 AIRFOIL (n1h15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1-H-15 AIRFOIL (n1h15-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.15 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n1h15-il-1000000-n5.txt Download as CSV file: xf-n1h15-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1-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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2829 0.08806 0.08525 -0.0506 0.6821 0.0146
-10.000 -0.3158 0.07870 0.07592 -0.0551 0.6812 0.0158
-9.750 -0.3221 0.07474 0.07198 -0.0573 0.6802 0.0159
-9.500 -0.3225 0.07199 0.06924 -0.0591 0.6791 0.0161
-9.250 -0.3456 0.06720 0.06447 -0.0618 0.6779 0.0161
-8.750 -0.5391 0.02635 0.02208 -0.0566 0.6753 0.0191
-8.500 -0.5251 0.02441 0.01992 -0.0552 0.6745 0.0193
-8.250 -0.5043 0.02348 0.01889 -0.0545 0.6736 0.0194
-8.000 -0.4831 0.02254 0.01783 -0.0538 0.6726 0.0195
-7.750 -0.4607 0.02175 0.01693 -0.0533 0.6715 0.0197
-7.500 -0.4377 0.02102 0.01611 -0.0528 0.6705 0.0198
-7.250 -0.4141 0.02037 0.01536 -0.0523 0.6695 0.0200
-7.000 -0.3901 0.01975 0.01465 -0.0519 0.6685 0.0202
-6.750 -0.3662 0.01904 0.01383 -0.0515 0.6675 0.0204
-6.500 -0.3429 0.01812 0.01275 -0.0510 0.6665 0.0207
-6.250 -0.3189 0.01725 0.01174 -0.0505 0.6655 0.0209
-6.000 -0.2944 0.01641 0.01075 -0.0501 0.6645 0.0211
-5.750 -0.2692 0.01568 0.00989 -0.0498 0.6634 0.0213
-5.500 -0.2437 0.01499 0.00906 -0.0495 0.6622 0.0216
-5.250 -0.2176 0.01441 0.00836 -0.0493 0.6610 0.0218
-5.000 -0.1910 0.01387 0.00774 -0.0492 0.6602 0.0220
-4.750 -0.1641 0.01338 0.00718 -0.0492 0.6594 0.0222
-4.500 -0.1369 0.01296 0.00671 -0.0492 0.6586 0.0224
-4.250 -0.1094 0.01266 0.00636 -0.0493 0.6576 0.0226
-4.000 -0.0817 0.01240 0.00606 -0.0494 0.6567 0.0227
-3.750 -0.0541 0.01210 0.00573 -0.0495 0.6556 0.0229
-3.500 -0.0278 0.01146 0.00505 -0.0493 0.6545 0.0232
-3.250 -0.0007 0.01110 0.00467 -0.0494 0.6533 0.0235
-3.000 0.0266 0.01084 0.00440 -0.0494 0.6522 0.0238
-2.750 0.0541 0.01061 0.00416 -0.0495 0.6511 0.0240
-2.500 0.0816 0.01039 0.00393 -0.0495 0.6501 0.0242
-2.250 0.1091 0.01021 0.00373 -0.0496 0.6491 0.0246
-2.000 0.1365 0.01002 0.00354 -0.0497 0.6481 0.0248
-1.750 0.1640 0.00986 0.00336 -0.0497 0.6470 0.0251
-1.500 0.1916 0.00971 0.00320 -0.0499 0.6460 0.0254
-1.250 0.2194 0.00956 0.00307 -0.0500 0.6451 0.0257
-1.000 0.2474 0.00943 0.00295 -0.0502 0.6440 0.0261
-0.750 0.2754 0.00931 0.00284 -0.0504 0.6428 0.0265
-0.500 0.3034 0.00921 0.00275 -0.0506 0.6417 0.0269
-0.250 0.3316 0.00914 0.00269 -0.0509 0.6406 0.0273
0.000 0.3594 0.00903 0.00259 -0.0511 0.6395 0.0278
0.250 0.3872 0.00892 0.00249 -0.0513 0.6384 0.0285
0.500 0.4152 0.00885 0.00243 -0.0515 0.6372 0.0292
0.750 0.4434 0.00879 0.00238 -0.0518 0.6360 0.0300
1.000 0.4714 0.00874 0.00234 -0.0520 0.6348 0.0308
1.250 0.4995 0.00871 0.00231 -0.0523 0.6335 0.0318
1.500 0.5275 0.00869 0.00229 -0.0525 0.6323 0.0328
1.750 0.5558 0.00867 0.00231 -0.0529 0.6314 0.0352
2.000 0.5839 0.00863 0.00235 -0.0532 0.6303 0.0457
2.250 0.6087 0.00831 0.00243 -0.0530 0.6291 0.2010
2.750 0.7147 0.00682 0.00307 -0.0649 0.6269 0.9725
3.000 0.7633 0.00696 0.00321 -0.0696 0.6246 0.9759
3.250 0.8049 0.00710 0.00333 -0.0729 0.6212 0.9808
3.500 0.8444 0.00723 0.00343 -0.0756 0.6184 0.9847
3.750 0.8803 0.00729 0.00351 -0.0778 0.6164 0.9857
4.000 0.9128 0.00736 0.00361 -0.0792 0.6127 0.9863
4.250 0.9445 0.00743 0.00370 -0.0805 0.6095 0.9870
4.500 0.9757 0.00750 0.00378 -0.0816 0.6064 0.9877
4.750 1.0066 0.00761 0.00388 -0.0828 0.6019 0.9884
5.000 1.0386 0.00780 0.00409 -0.0843 0.5927 0.9891
5.250 1.0712 0.00811 0.00438 -0.0862 0.5787 0.9898
5.500 1.1045 0.00886 0.00503 -0.0890 0.5500 0.9905
5.750 1.1272 0.01152 0.00734 -0.0927 0.4783 0.9931
6.000 1.0993 0.01603 0.01135 -0.0898 0.3819 1.0000
6.250 1.0644 0.01788 0.01304 -0.0805 0.3485 1.0000
6.500 1.0283 0.02039 0.01525 -0.0720 0.2937 1.0000
6.750 0.9959 0.02313 0.01762 -0.0646 0.2219 1.0000
7.000 0.9800 0.02530 0.01950 -0.0596 0.1647 1.0000
7.250 0.9788 0.02678 0.02080 -0.0565 0.1297 1.0000
7.500 0.9818 0.02808 0.02197 -0.0539 0.1029 1.0000
7.750 0.9873 0.02926 0.02304 -0.0516 0.0794 1.0000
8.000 0.9929 0.03050 0.02416 -0.0495 0.0582 1.0000
8.250 1.0025 0.03152 0.02512 -0.0478 0.0477 1.0000
8.500 1.0143 0.03242 0.02599 -0.0464 0.0421 1.0000
8.750 1.0278 0.03321 0.02678 -0.0451 0.0392 1.0000
9.000 1.0409 0.03405 0.02762 -0.0439 0.0375 1.0000
9.250 1.0530 0.03499 0.02855 -0.0426 0.0354 1.0000
9.500 1.0660 0.03586 0.02944 -0.0414 0.0341 1.0000
9.750 1.0800 0.03667 0.03027 -0.0404 0.0334 1.0000
10.000 1.0938 0.03751 0.03112 -0.0393 0.0328 1.0000
10.250 1.1070 0.03840 0.03202 -0.0382 0.0319 1.0000
10.500 1.1193 0.03939 0.03302 -0.0371 0.0311 1.0000
10.750 1.1318 0.04036 0.03400 -0.0360 0.0303 1.0000
11.000 1.1442 0.04135 0.03501 -0.0350 0.0293 1.0000
11.250 1.1557 0.04241 0.03608 -0.0339 0.0283 1.0000
11.500 1.1683 0.04341 0.03710 -0.0329 0.0279 1.0000
11.750 1.1809 0.04443 0.03815 -0.0320 0.0275 1.0000
12.000 1.1938 0.04543 0.03918 -0.0311 0.0270 1.0000
12.250 1.2066 0.04644 0.04022 -0.0302 0.0264 1.0000
12.500 1.2193 0.04747 0.04128 -0.0293 0.0259 1.0000
12.750 1.2308 0.04862 0.04246 -0.0285 0.0255 1.0000
13.000 1.2422 0.04977 0.04363 -0.0276 0.0247 1.0000
13.250 1.2529 0.05100 0.04485 -0.0267 0.0236 1.0000
13.500 1.2634 0.05225 0.04613 -0.0258 0.0230 1.0000
13.750 1.2750 0.05343 0.04735 -0.0250 0.0229 1.0000
14.000 1.2869 0.05461 0.04858 -0.0243 0.0224 1.0000
14.250 1.2980 0.05585 0.04986 -0.0236 0.0218 1.0000
14.500 1.3094 0.05706 0.05111 -0.0229 0.0213 1.0000
14.750 1.3208 0.05828 0.05236 -0.0223 0.0207 1.0000
15.000 1.3311 0.05962 0.05371 -0.0216 0.0200 1.0000
15.250 1.3407 0.06104 0.05516 -0.0209 0.0194 1.0000
15.500 1.3498 0.06251 0.05665 -0.0202 0.0188 1.0000
15.750 1.3610 0.06379 0.05798 -0.0197 0.0183 1.0000
16.000 1.3707 0.06523 0.05947 -0.0191 0.0176 1.0000
16.250 1.3796 0.06677 0.06104 -0.0185 0.0170 1.0000
16.500 1.3889 0.06824 0.06254 -0.0180 0.0163 1.0000
16.750 1.3979 0.06975 0.06407 -0.0175 0.0156 1.0000
17.000 1.4052 0.07148 0.06583 -0.0169 0.0151 1.0000
17.250 1.4128 0.07318 0.06760 -0.0164 0.0147 1.0000
17.500 1.4210 0.07483 0.06929 -0.0160 0.0141 1.0000
17.750 1.4286 0.07655 0.07105 -0.0156 0.0134 1.0000
18.000 1.4346 0.07848 0.07302 -0.0152 0.0129 1.0000
18.250 1.4405 0.08039 0.07496 -0.0148 0.0124 1.0000
18.500 1.4465 0.08232 0.07694 -0.0145 0.0119 1.0000
18.750 1.4516 0.08439 0.07908 -0.0142 0.0116 1.0000
19.000 1.4566 0.08648 0.08123 -0.0139 0.0113 1.0000
19.250 1.4613 0.08861 0.08342 -0.0138 0.0109 1.0000
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