NACA 2-H-15 AIRFOIL (n2h15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: NACA 2-H-15 AIRFOIL (n2h15-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.08 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n2h15-il-1000000-n5.txt Download as CSV file: xf-n2h15-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2-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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1295 0.08500 0.08177 -0.0884 0.6719 0.0168
-10.500 -0.1279 0.08187 0.07866 -0.0900 0.6712 0.0170
-10.250 -0.1258 0.07893 0.07573 -0.0914 0.6704 0.0174
-10.000 -0.1304 0.07498 0.07180 -0.0934 0.6696 0.0178
-9.750 -0.1383 0.07082 0.06766 -0.0954 0.6687 0.0179
-9.500 -0.1527 0.06612 0.06299 -0.0981 0.6676 0.0180
-9.250 -0.1834 0.06064 0.05751 -0.1011 0.6664 0.0182
-9.000 -0.2049 0.05729 0.05414 -0.0996 0.6652 0.0181
-8.750 -0.2311 0.05406 0.05087 -0.0958 0.6642 0.0181
-8.500 -0.2577 0.05122 0.04798 -0.0903 0.6630 0.0181
-8.250 -0.2916 0.04818 0.04485 -0.0825 0.6619 0.0183
-8.000 -0.3151 0.04499 0.04155 -0.0760 0.6608 0.0184
-7.750 -0.3509 0.03950 0.03581 -0.0672 0.6597 0.0186
-7.500 -0.3893 0.03318 0.02911 -0.0571 0.6585 0.0190
-7.250 -0.3954 0.03052 0.02626 -0.0516 0.6577 0.0191
-7.000 -0.3878 0.02928 0.02491 -0.0482 0.6569 0.0192
-6.750 -0.3799 0.02791 0.02342 -0.0448 0.6559 0.0193
-6.500 -0.3743 0.02606 0.02139 -0.0409 0.6549 0.0195
-6.250 -0.3567 0.02579 0.02108 -0.0392 0.6538 0.0196
-6.000 -0.3484 0.02395 0.01905 -0.0355 0.6528 0.0198
-5.750 -0.3358 0.02250 0.01742 -0.0326 0.6518 0.0199
-5.500 -0.3235 0.02053 0.01520 -0.0296 0.6508 0.0201
-5.250 -0.3060 0.01908 0.01354 -0.0276 0.6498 0.0203
-5.000 -0.2848 0.01762 0.01185 -0.0264 0.6489 0.0205
-4.750 -0.2593 0.01635 0.01038 -0.0260 0.6479 0.0207
-4.500 -0.2316 0.01544 0.00933 -0.0261 0.6469 0.0208
-4.250 -0.2005 0.01453 0.00828 -0.0270 0.6459 0.0211
-4.000 -0.1688 0.01385 0.00748 -0.0280 0.6448 0.0214
-3.750 -0.1376 0.01334 0.00689 -0.0289 0.6435 0.0217
-3.500 -0.0984 0.01264 0.00612 -0.0315 0.6426 0.0219
-3.250 -0.0624 0.01215 0.00558 -0.0335 0.6419 0.0222
-3.000 -0.0281 0.01173 0.00513 -0.0351 0.6411 0.0223
-2.750 0.0034 0.01142 0.00480 -0.0360 0.6402 0.0224
-2.500 0.0392 0.01093 0.00428 -0.0380 0.6393 0.0228
-2.250 0.0710 0.01060 0.00396 -0.0390 0.6383 0.0230
-2.000 0.1008 0.01035 0.00371 -0.0396 0.6372 0.0233
-1.750 0.1294 0.01016 0.00353 -0.0399 0.6360 0.0236
-1.500 0.1578 0.00997 0.00335 -0.0402 0.6348 0.0238
-1.250 0.1860 0.00981 0.00319 -0.0404 0.6336 0.0241
-1.000 0.2142 0.00965 0.00302 -0.0406 0.6325 0.0244
-0.750 0.2421 0.00951 0.00289 -0.0407 0.6315 0.0247
-0.500 0.2703 0.00936 0.00273 -0.0409 0.6304 0.0251
-0.250 0.2983 0.00924 0.00261 -0.0411 0.6293 0.0253
0.000 0.3260 0.00917 0.00254 -0.0412 0.6281 0.0259
0.250 0.3542 0.00908 0.00247 -0.0414 0.6271 0.0264
0.500 0.3824 0.00899 0.00241 -0.0416 0.6261 0.0267
0.750 0.4114 0.00887 0.00231 -0.0420 0.6249 0.0277
1.000 0.4403 0.00879 0.00226 -0.0424 0.6237 0.0282
1.250 0.4690 0.00873 0.00223 -0.0428 0.6226 0.0289
1.500 0.4976 0.00868 0.00222 -0.0431 0.6213 0.0295
1.750 0.5263 0.00864 0.00220 -0.0435 0.6201 0.0307
2.000 0.5547 0.00861 0.00219 -0.0438 0.6187 0.0313
2.250 0.5832 0.00858 0.00218 -0.0441 0.6173 0.0335
2.500 0.6117 0.00855 0.00219 -0.0444 0.6161 0.0374
2.750 0.6735 0.00690 0.00261 -0.0533 0.6152 0.8170
3.000 0.7067 0.00688 0.00270 -0.0546 0.6139 0.8570
3.500 0.8514 0.00749 0.00358 -0.0750 0.6097 0.9036
3.750 0.9146 0.00786 0.00401 -0.0830 0.6059 0.9144
4.000 0.9504 0.00797 0.00414 -0.0849 0.6025 0.9173
4.250 0.9876 0.00809 0.00426 -0.0871 0.5991 0.9227
5.250 1.0375 0.00908 0.00518 -0.0746 0.5596 0.9736
5.500 1.0648 0.00955 0.00550 -0.0752 0.5246 0.9749
5.750 1.0769 0.01156 0.00707 -0.0743 0.4303 0.9774
6.000 1.0637 0.01683 0.01174 -0.0739 0.3025 0.9818
6.500 1.0101 0.02291 0.01727 -0.0627 0.1849 0.9920
7.000 1.0109 0.02641 0.02043 -0.0580 0.1133 0.9956
7.250 1.0208 0.02765 0.02153 -0.0571 0.0872 0.9963
7.500 1.0286 0.02902 0.02278 -0.0557 0.0630 0.9969
7.750 1.0391 0.03017 0.02384 -0.0545 0.0478 0.9973
8.000 1.0517 0.03116 0.02479 -0.0534 0.0399 0.9975
8.250 1.0663 0.03208 0.02570 -0.0526 0.0365 0.9978
8.500 1.0812 0.03303 0.02663 -0.0519 0.0334 0.9982
8.750 1.0960 0.03388 0.02749 -0.0510 0.0314 0.9983
9.000 1.1095 0.03480 0.02841 -0.0499 0.0296 0.9983
9.250 1.1220 0.03577 0.02938 -0.0486 0.0279 0.9982
9.500 1.1347 0.03674 0.03037 -0.0474 0.0270 0.9981
9.750 1.1476 0.03768 0.03132 -0.0462 0.0262 0.9979
10.000 1.1597 0.03867 0.03233 -0.0449 0.0250 0.9977
10.250 1.1717 0.03967 0.03333 -0.0436 0.0239 0.9974
10.500 1.1832 0.04074 0.03441 -0.0424 0.0229 0.9973
10.750 1.1965 0.04176 0.03545 -0.0414 0.0221 0.9972
11.000 1.2089 0.04281 0.03652 -0.0404 0.0211 0.9971
11.250 1.2213 0.04384 0.03756 -0.0393 0.0204 0.9970
11.500 1.2332 0.04494 0.03867 -0.0382 0.0195 0.9969
11.750 1.2432 0.04613 0.03987 -0.0369 0.0186 0.9967
12.000 1.2528 0.04732 0.04109 -0.0354 0.0180 0.9963
12.250 1.2638 0.04847 0.04226 -0.0342 0.0176 0.9962
12.500 1.2745 0.04963 0.04346 -0.0329 0.0172 0.9960
12.750 1.2841 0.05082 0.04467 -0.0315 0.0166 0.9957
13.000 1.2917 0.05218 0.04605 -0.0298 0.0159 0.9955
13.250 1.3017 0.05352 0.04740 -0.0288 0.0153 0.9954
13.500 1.3116 0.05488 0.04879 -0.0278 0.0147 0.9954
13.750 1.3228 0.05611 0.05005 -0.0269 0.0143 0.9953
14.000 1.3322 0.05751 0.05150 -0.0258 0.0141 0.9953
14.250 1.3404 0.05902 0.05304 -0.0246 0.0137 0.9951
14.500 1.3472 0.06064 0.05469 -0.0230 0.0133 0.9950
15.500 1.3787 0.06761 0.06178 -0.0190 0.0117 0.9946
15.750 1.3885 0.06908 0.06330 -0.0185 0.0116 0.9946
16.000 1.3968 0.07072 0.06499 -0.0179 0.0114 0.9946
16.250 1.4054 0.07235 0.06668 -0.0175 0.0112 0.9946
16.500 1.4147 0.07390 0.06827 -0.0171 0.0109 0.9946
16.750 1.4221 0.07566 0.07008 -0.0166 0.0106 0.9946
17.000 1.4296 0.07744 0.07192 -0.0162 0.0104 0.9946
17.250 1.4357 0.07939 0.07393 -0.0158 0.0103 0.9945
17.500 1.4429 0.08120 0.07578 -0.0154 0.0101 0.9945
17.750 1.4479 0.08333 0.07797 -0.0151 0.0099 0.9945
18.000 1.4534 0.08540 0.08008 -0.0148 0.0096 0.9945
18.250 1.4589 0.08747 0.08221 -0.0146 0.0095 0.9945
18.500 1.4608 0.09001 0.08481 -0.0143 0.0093 0.9945
18.750 1.4627 0.09257 0.08743 -0.0141 0.0090 0.9944
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