NACA 5-H-15 AIRFOIL (n5h15-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 5-H-15 AIRFOIL (n5h15-il) Reynolds number: 500,000 Max Cl/Cd: 78.23 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n5h15-il-500000.txt Download as CSV file: xf-n5h15-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3857 0.07773 0.07483 -0.0419 0.7224 0.0381
-10.250 -0.4227 0.06801 0.06501 -0.0489 0.7219 0.0381
-10.000 -0.4544 0.06238 0.05927 -0.0502 0.7201 0.0382
-9.750 -0.4833 0.05824 0.05499 -0.0489 0.7182 0.0382
-9.500 -0.5099 0.05507 0.05167 -0.0457 0.7160 0.0382
-9.250 -0.5324 0.05234 0.04879 -0.0412 0.7137 0.0383
-9.000 -0.5496 0.04917 0.04547 -0.0372 0.7113 0.0383
-8.750 -0.5859 0.04034 0.03640 -0.0327 0.7094 0.0390
-8.500 -0.5757 0.03729 0.03335 -0.0319 0.7067 0.0395
-8.250 -0.5672 0.03493 0.03093 -0.0304 0.7040 0.0399
-8.000 -0.5570 0.03297 0.02890 -0.0289 0.7016 0.0405
-7.750 -0.5464 0.03108 0.02691 -0.0274 0.6995 0.0413
-7.500 -0.5366 0.02904 0.02474 -0.0255 0.6972 0.0425
-7.250 -0.5275 0.02679 0.02226 -0.0231 0.6944 0.0449
-7.000 -0.5141 0.02741 0.02248 -0.0194 0.6911 0.0469
-6.750 -0.5216 0.02040 0.01510 -0.0160 0.6891 0.0484
-6.500 -0.5018 0.01867 0.01334 -0.0155 0.6868 0.0492
-6.250 -0.4829 0.01728 0.01186 -0.0146 0.6846 0.0502
-6.000 -0.4804 0.02369 0.01685 -0.0105 0.6857 0.0396
-5.750 -0.4558 0.02266 0.01558 -0.0097 0.6834 0.0390
-5.500 -0.4296 0.02110 0.01389 -0.0096 0.6808 0.0392
-5.250 -0.4020 0.01973 0.01244 -0.0098 0.6778 0.0396
-5.000 -0.3735 0.01864 0.01125 -0.0100 0.6750 0.0397
-4.750 -0.3447 0.01768 0.01021 -0.0103 0.6723 0.0400
-4.500 -0.3161 0.01687 0.00933 -0.0106 0.6699 0.0404
-4.250 -0.2878 0.01621 0.00860 -0.0108 0.6676 0.0408
-4.000 -0.2600 0.01562 0.00802 -0.0109 0.6653 0.0414
-3.750 -0.2327 0.01509 0.00749 -0.0109 0.6625 0.0422
-3.500 -0.2060 0.01465 0.00703 -0.0108 0.6597 0.0432
-3.250 -0.1798 0.01420 0.00655 -0.0106 0.6570 0.0441
-3.000 -0.1542 0.01377 0.00607 -0.0102 0.6545 0.0448
-2.750 -0.1292 0.01343 0.00568 -0.0097 0.6520 0.0456
-2.500 -0.1040 0.01311 0.00537 -0.0093 0.6493 0.0464
-2.250 -0.0788 0.01285 0.00511 -0.0089 0.6464 0.0470
-2.000 -0.0570 0.01230 0.00453 -0.0078 0.6435 0.0491
-1.750 -0.0326 0.01201 0.00424 -0.0072 0.6408 0.0514
-1.500 -0.0073 0.01183 0.00403 -0.0067 0.6381 0.0543
-1.250 0.0182 0.01169 0.00386 -0.0064 0.6353 0.0571
-1.000 0.0424 0.01139 0.00361 -0.0057 0.6321 0.0639
-0.750 0.0666 0.01112 0.00339 -0.0051 0.6288 0.0817
-0.500 0.0660 0.00950 0.00306 -0.0001 0.6258 0.4410
-0.250 0.0521 0.00807 0.00316 0.0090 0.6232 0.8321
0.000 0.0730 0.00834 0.00343 0.0110 0.6201 0.8751
0.250 0.1073 0.00878 0.00393 0.0104 0.6163 0.8964
0.500 0.1403 0.00916 0.00428 0.0099 0.6123 0.9090
0.750 0.1931 0.00970 0.00477 0.0052 0.6085 0.9153
1.000 0.2271 0.01006 0.00506 0.0043 0.6048 0.9237
1.250 0.3506 0.01131 0.00627 -0.0145 0.5989 0.9280
1.500 0.3861 0.01135 0.00628 -0.0162 0.5943 0.9306
1.750 0.4127 0.01135 0.00621 -0.0162 0.5899 0.9335
2.000 0.4220 0.01127 0.00617 -0.0126 0.5845 0.9391
2.250 0.4572 0.01121 0.00608 -0.0143 0.5789 0.9399
2.500 0.4932 0.01121 0.00604 -0.0163 0.5734 0.9409
2.750 0.5249 0.01116 0.00601 -0.0173 0.5665 0.9419
3.000 0.5555 0.01115 0.00594 -0.0182 0.5607 0.9430
3.250 0.5858 0.01112 0.00595 -0.0190 0.5533 0.9444
3.500 0.6140 0.01112 0.00591 -0.0194 0.5468 0.9459
3.750 0.6404 0.01112 0.00593 -0.0194 0.5398 0.9477
4.000 0.6638 0.01114 0.00594 -0.0188 0.5335 0.9501
4.250 0.6711 0.01119 0.00598 -0.0149 0.5280 0.9543
4.500 0.7030 0.01117 0.00597 -0.0161 0.5209 0.9550
4.750 0.7337 0.01119 0.00597 -0.0171 0.5140 0.9557
5.000 0.7640 0.01122 0.00599 -0.0180 0.5035 0.9565
5.250 0.7942 0.01128 0.00604 -0.0189 0.4922 0.9575
5.500 0.8230 0.01138 0.00612 -0.0196 0.4825 0.9586
5.750 0.8499 0.01148 0.00622 -0.0198 0.4741 0.9598
6.000 0.8758 0.01158 0.00634 -0.0199 0.4662 0.9611
6.500 0.9223 0.01190 0.00664 -0.0190 0.4456 0.9649
6.750 0.9376 0.01208 0.00683 -0.0170 0.4345 0.9673
7.000 0.9522 0.01229 0.00702 -0.0149 0.4228 0.9695
7.250 0.9810 0.01254 0.00725 -0.0158 0.4055 0.9704
7.500 1.0071 0.01294 0.00759 -0.0164 0.3762 0.9716
7.750 1.0051 0.01495 0.00897 -0.0137 0.2488 0.9754
8.000 0.9910 0.01650 0.01029 -0.0082 0.1999 0.9813
8.250 0.9823 0.01865 0.01216 -0.0062 0.1414 0.9863
8.500 0.9794 0.02071 0.01400 -0.0048 0.0964 0.9906
8.750 0.9727 0.02317 0.01621 -0.0032 0.0527 0.9945
9.000 0.9793 0.02523 0.01813 -0.0034 0.0272 0.9972
9.250 0.9946 0.02665 0.01955 -0.0041 0.0234 0.9992
9.500 0.9993 0.02796 0.02091 -0.0025 0.0219 1.0000
9.750 0.9907 0.02916 0.02216 0.0016 0.0208 1.0000
10.000 0.9851 0.03017 0.02322 0.0054 0.0204 1.0000
10.250 0.9784 0.03118 0.02427 0.0095 0.0199 1.0000
10.500 0.9720 0.03219 0.02533 0.0134 0.0197 1.0000
10.750 0.9666 0.03343 0.02660 0.0168 0.0190 1.0000
11.000 0.9645 0.03485 0.02806 0.0195 0.0184 1.0000
11.250 0.9644 0.03641 0.02966 0.0216 0.0181 1.0000
11.500 0.9631 0.03823 0.03152 0.0235 0.0175 1.0000
11.750 0.9613 0.04024 0.03358 0.0252 0.0171 1.0000
12.000 0.9576 0.04254 0.03593 0.0269 0.0167 1.0000
12.250 0.9613 0.04427 0.03771 0.0280 0.0167 1.0000
12.500 0.9662 0.04598 0.03948 0.0290 0.0165 1.0000
12.750 0.9702 0.04781 0.04136 0.0300 0.0162 1.0000
13.000 0.9753 0.04959 0.04318 0.0308 0.0159 1.0000
13.250 0.9801 0.05139 0.04503 0.0317 0.0157 1.0000
13.500 0.9858 0.05314 0.04683 0.0324 0.0156 1.0000
13.750 0.9909 0.05495 0.04867 0.0332 0.0149 1.0000
14.000 0.9984 0.05655 0.05031 0.0338 0.0148 1.0000
14.250 1.0052 0.05821 0.05198 0.0344 0.0143 1.0000
14.500 1.0131 0.05969 0.05347 0.0353 0.0140 1.0000
14.750 1.0226 0.06105 0.05488 0.0360 0.0140 1.0000
15.000 1.0406 0.06079 0.05453 0.0384 0.0134 1.0000
15.250 1.0595 0.06100 0.05476 0.0400 0.0133 1.0000
15.500 1.0602 0.06370 0.05762 0.0396 0.0131 1.0000
15.750 1.0731 0.06479 0.05878 0.0406 0.0130 1.0000
16.000 1.0815 0.06651 0.06061 0.0410 0.0129 1.0000
16.250 1.0921 0.06798 0.06218 0.0417 0.0129 1.0000
16.500 1.0977 0.07009 0.06442 0.0421 0.0128 1.0000
16.750 1.1009 0.07253 0.06700 0.0422 0.0126 1.0000
17.000 1.1081 0.07454 0.06913 0.0429 0.0127 1.0000
17.250 1.1073 0.07756 0.07232 0.0428 0.0126 1.0000
17.500 1.1128 0.07987 0.07474 0.0434 0.0129 1.0000
17.750 1.1092 0.08331 0.07833 0.0431 0.0128 1.0000
18.000 1.1006 0.08749 0.08271 0.0423 0.0127 1.0000
18.250 1.0935 0.09155 0.08693 0.0414 0.0126 1.0000
18.500 1.0863 0.09584 0.09138 0.0411 0.0129 1.0000
18.750 1.0727 0.10100 0.09673 0.0388 0.0125 1.0000
19.000 1.0624 0.10586 0.10173 0.0376 0.0128 1.0000
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