NACA 1-H-15 AIRFOIL (n1h15-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 1-H-15 AIRFOIL (n1h15-il) Reynolds number: 500,000 Max Cl/Cd: 102.18 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n1h15-il-500000-n5.txt Download as CSV file: xf-n1h15-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2559 0.09511 0.09171 -0.0484 0.6977 0.0183
-10.000 -0.2707 0.08839 0.08502 -0.0521 0.6968 0.0192
-9.750 -0.2709 0.08473 0.08136 -0.0540 0.6959 0.0192
-9.500 -0.2584 0.08361 0.08024 -0.0545 0.6949 0.0195
-9.250 -0.2585 0.08026 0.07690 -0.0563 0.6939 0.0197
-9.000 -0.2549 0.07775 0.07440 -0.0577 0.6930 0.0200
-8.750 -0.2623 0.07385 0.07051 -0.0601 0.6920 0.0201
-8.500 -0.2741 0.07010 0.06676 -0.0621 0.6909 0.0203
-8.250 -0.2888 0.06625 0.06287 -0.0627 0.6898 0.0203
-8.000 -0.2933 0.06211 0.05870 -0.0642 0.6886 0.0204
-7.750 -0.2950 0.05780 0.05433 -0.0654 0.6873 0.0207
-7.500 -0.2948 0.05320 0.04961 -0.0660 0.6860 0.0209
-7.250 -0.2934 0.04820 0.04443 -0.0660 0.6847 0.0214
-7.000 -0.3331 0.03132 0.02644 -0.0609 0.6835 0.0229
-6.750 -0.3200 0.02890 0.02378 -0.0596 0.6824 0.0231
-6.500 -0.3006 0.02760 0.02233 -0.0588 0.6813 0.0234
-6.250 -0.2785 0.02682 0.02146 -0.0584 0.6803 0.0236
-6.000 -0.2563 0.02597 0.02050 -0.0579 0.6794 0.0239
-5.750 -0.2351 0.02472 0.01908 -0.0572 0.6785 0.0243
-5.500 -0.2151 0.02297 0.01704 -0.0561 0.6775 0.0246
-5.250 -0.1934 0.02153 0.01534 -0.0552 0.6766 0.0249
-5.000 -0.1706 0.02025 0.01382 -0.0544 0.6756 0.0252
-4.750 -0.1461 0.01918 0.01254 -0.0540 0.6746 0.0254
-4.500 -0.1204 0.01826 0.01146 -0.0539 0.6735 0.0258
-4.250 -0.0939 0.01750 0.01056 -0.0538 0.6723 0.0261
-4.000 -0.0670 0.01690 0.00984 -0.0538 0.6712 0.0265
-3.750 -0.0398 0.01638 0.00920 -0.0539 0.6700 0.0269
-3.500 -0.0124 0.01586 0.00859 -0.0539 0.6689 0.0271
-3.250 0.0151 0.01542 0.00807 -0.0540 0.6677 0.0273
-3.000 0.0425 0.01492 0.00751 -0.0541 0.6666 0.0275
-2.750 0.0695 0.01429 0.00684 -0.0541 0.6655 0.0279
-2.500 0.0965 0.01386 0.00639 -0.0542 0.6644 0.0282
-2.250 0.1235 0.01351 0.00603 -0.0542 0.6635 0.0286
-2.000 0.1503 0.01321 0.00572 -0.0541 0.6626 0.0290
-1.750 0.1771 0.01295 0.00543 -0.0540 0.6618 0.0294
-1.500 0.2037 0.01272 0.00518 -0.0539 0.6610 0.0298
-1.250 0.2310 0.01256 0.00504 -0.0541 0.6599 0.0303
-1.000 0.2587 0.01245 0.00497 -0.0544 0.6585 0.0311
-0.750 0.2861 0.01234 0.00487 -0.0546 0.6570 0.0318
-0.500 0.3134 0.01223 0.00477 -0.0547 0.6556 0.0324
-0.250 0.3407 0.01213 0.00468 -0.0549 0.6542 0.0327
0.000 0.3677 0.01200 0.00456 -0.0549 0.6530 0.0334
0.250 0.3947 0.01189 0.00446 -0.0550 0.6519 0.0344
0.500 0.4219 0.01180 0.00439 -0.0551 0.6508 0.0355
0.750 0.4493 0.01174 0.00432 -0.0552 0.6498 0.0368
1.000 0.4767 0.01167 0.00426 -0.0553 0.6488 0.0385
1.250 0.5039 0.01160 0.00419 -0.0554 0.6478 0.0424
1.500 0.5306 0.01147 0.00414 -0.0553 0.6469 0.0635
1.750 0.5516 0.01095 0.00430 -0.0546 0.6455 0.3019
2.250 0.7182 0.01001 0.00524 -0.0787 0.6445 0.9823
2.500 0.7780 0.01016 0.00540 -0.0859 0.6435 0.9900
2.750 0.8193 0.01030 0.00555 -0.0892 0.6420 0.9941
3.000 0.8543 0.01036 0.00563 -0.0913 0.6404 0.9956
3.250 0.8861 0.01037 0.00564 -0.0925 0.6382 0.9967
3.500 0.9172 0.01034 0.00561 -0.0936 0.6361 0.9977
3.750 0.9478 0.01018 0.00542 -0.0943 0.6334 0.9987
4.000 0.9797 0.01024 0.00550 -0.0957 0.6306 0.9997
4.250 1.0102 0.01046 0.00580 -0.0971 0.6261 1.0000
4.500 1.0372 0.01058 0.00595 -0.0974 0.6231 1.0000
4.750 1.0635 0.01059 0.00596 -0.0975 0.6201 1.0000
5.000 1.0903 0.01067 0.00608 -0.0978 0.6161 1.0000
5.250 1.1193 0.01110 0.00660 -0.0992 0.6103 1.0000
5.500 1.1469 0.01124 0.00672 -0.0999 0.6009 1.0000
5.750 1.1740 0.01168 0.00718 -0.1010 0.5868 1.0000
6.000 1.1971 0.01239 0.00785 -0.1017 0.5639 1.0000
6.250 1.2106 0.01339 0.00872 -0.1009 0.5338 1.0000
6.500 1.1998 0.01501 0.01016 -0.0961 0.5005 1.0000
6.750 1.1670 0.01635 0.01140 -0.0864 0.4820 1.0000
7.000 1.1382 0.01802 0.01292 -0.0781 0.4553 1.0000
7.250 1.1129 0.02004 0.01476 -0.0710 0.4227 1.0000
7.500 1.0795 0.02286 0.01729 -0.0635 0.3744 1.0000
7.750 1.0459 0.02610 0.02016 -0.0567 0.3118 1.0000
8.000 1.0149 0.02948 0.02310 -0.0506 0.2345 1.0000
8.250 0.9992 0.03208 0.02535 -0.0465 0.1716 1.0000
8.500 0.9973 0.03387 0.02692 -0.0437 0.1306 1.0000
8.750 0.9980 0.03557 0.02843 -0.0414 0.0970 1.0000
9.000 1.0027 0.03702 0.02974 -0.0395 0.0718 1.0000
9.250 1.0109 0.03825 0.03089 -0.0379 0.0572 1.0000
9.500 1.0206 0.03941 0.03201 -0.0365 0.0496 1.0000
9.750 1.0317 0.04049 0.03309 -0.0352 0.0454 1.0000
10.000 1.0430 0.04157 0.03416 -0.0340 0.0426 1.0000
10.250 1.0553 0.04258 0.03519 -0.0330 0.0410 1.0000
10.500 1.0678 0.04359 0.03623 -0.0319 0.0397 1.0000
10.750 1.0794 0.04470 0.03736 -0.0308 0.0386 1.0000
11.000 1.0910 0.04581 0.03851 -0.0298 0.0374 1.0000
11.250 1.1019 0.04699 0.03970 -0.0288 0.0362 1.0000
11.500 1.1119 0.04826 0.04098 -0.0276 0.0349 1.0000
11.750 1.1222 0.04952 0.04227 -0.0266 0.0339 1.0000
12.000 1.1333 0.05074 0.04354 -0.0257 0.0335 1.0000
12.250 1.1443 0.05196 0.04481 -0.0248 0.0328 1.0000
12.500 1.1560 0.05313 0.04602 -0.0239 0.0318 1.0000
12.750 1.1665 0.05442 0.04735 -0.0231 0.0310 1.0000
13.000 1.1764 0.05579 0.04875 -0.0222 0.0302 1.0000
13.250 1.1858 0.05721 0.05020 -0.0213 0.0295 1.0000
13.500 1.1938 0.05874 0.05176 -0.0204 0.0287 1.0000
13.750 1.2014 0.06035 0.05341 -0.0195 0.0280 1.0000
14.000 1.2119 0.06172 0.05484 -0.0188 0.0276 1.0000
14.250 1.2223 0.06311 0.05629 -0.0181 0.0269 1.0000
14.500 1.2326 0.06449 0.05773 -0.0175 0.0261 1.0000
14.750 1.2423 0.06597 0.05925 -0.0168 0.0255 1.0000
15.000 1.2514 0.06750 0.06084 -0.0162 0.0247 1.0000
15.250 1.2599 0.06911 0.06248 -0.0156 0.0242 1.0000
15.500 1.2669 0.07087 0.06425 -0.0150 0.0233 1.0000
15.750 1.2746 0.07259 0.06604 -0.0144 0.0229 1.0000
16.000 1.2844 0.07413 0.06766 -0.0140 0.0221 1.0000
16.250 1.2926 0.07582 0.06943 -0.0135 0.0216 1.0000
16.500 1.3015 0.07746 0.07113 -0.0131 0.0209 1.0000
16.750 1.3097 0.07920 0.07292 -0.0128 0.0202 1.0000
17.000 1.3164 0.08110 0.07488 -0.0124 0.0197 1.0000
17.250 1.3234 0.08299 0.07679 -0.0122 0.0190 1.0000
17.500 1.3289 0.08507 0.07895 -0.0118 0.0186 1.0000
17.750 1.3356 0.08703 0.08100 -0.0116 0.0181 1.0000
18.000 1.3418 0.08905 0.08310 -0.0114 0.0176 1.0000
18.250 1.3478 0.09114 0.08526 -0.0113 0.0169 1.0000
18.500 1.3537 0.09324 0.08744 -0.0112 0.0164 1.0000
18.750 1.3591 0.09540 0.08966 -0.0112 0.0159 1.0000
19.000 1.3621 0.09792 0.09223 -0.0112 0.0156 1.0000
19.250 1.3648 0.10047 0.09484 -0.0113 0.0151 1.0000
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