NPL 9615 AIRFOIL (npl9615-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9615 AIRFOIL (npl9615-il) Reynolds number: 200,000 Max Cl/Cd: 56.67 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9615-il-200000.txt Download as CSV file: xf-npl9615-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9615 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5934 0.08839 0.08457 -0.0294 1.0000 0.0574
-9.750 -0.6291 0.08088 0.07697 -0.0362 1.0000 0.0575
-9.500 -0.6644 0.07687 0.07280 -0.0357 1.0000 0.0576
-9.250 -0.6734 0.07253 0.06840 -0.0350 1.0000 0.0579
-9.000 -0.6570 0.06937 0.06534 -0.0346 1.0000 0.0584
-8.750 -0.6540 0.06645 0.06240 -0.0336 1.0000 0.0589
-8.500 -0.6546 0.06349 0.05939 -0.0323 1.0000 0.0596
-8.250 -0.6564 0.06049 0.05630 -0.0307 1.0000 0.0606
-8.000 -0.6924 0.05816 0.05317 -0.0247 1.0000 0.0641
-7.750 -0.6801 0.05373 0.04884 -0.0241 1.0000 0.0647
-7.500 -0.6686 0.05084 0.04600 -0.0228 1.0000 0.0653
-7.250 -0.6598 0.04844 0.04356 -0.0209 1.0000 0.0662
-7.000 -0.6817 0.03719 0.03090 -0.0120 1.0000 0.0416
-6.750 -0.6676 0.03501 0.02866 -0.0100 1.0000 0.0403
-6.500 -0.6651 0.02956 0.02226 -0.0049 1.0000 0.0365
-6.250 -0.6496 0.02744 0.01989 -0.0027 1.0000 0.0364
-6.000 -0.6329 0.02541 0.01754 -0.0006 1.0000 0.0365
-5.750 -0.6140 0.02373 0.01573 0.0010 1.0000 0.0371
-5.500 -0.5943 0.02267 0.01465 0.0023 1.0000 0.0379
-5.250 -0.5742 0.02152 0.01337 0.0038 1.0000 0.0394
-5.000 -0.5533 0.02017 0.01181 0.0053 1.0000 0.0419
-4.750 -0.5332 0.01944 0.01106 0.0067 1.0000 0.0451
-4.500 -0.5130 0.01869 0.01030 0.0080 1.0000 0.0489
-4.250 -0.4927 0.01808 0.00963 0.0093 1.0000 0.0531
-4.000 -0.4723 0.01762 0.00914 0.0105 1.0000 0.0565
-3.750 -0.4521 0.01714 0.00869 0.0116 1.0000 0.0598
-3.500 -0.4205 0.01681 0.00829 0.0105 0.9974 0.0639
-3.250 -0.3790 0.01619 0.00778 0.0072 0.9919 0.0680
-3.000 -0.3383 0.01573 0.00730 0.0044 0.9859 0.0717
-2.750 -0.2989 0.01520 0.00687 0.0017 0.9786 0.0766
-2.500 -0.2557 0.01472 0.00646 -0.0018 0.9735 0.0834
-2.250 -0.2200 0.01424 0.00602 -0.0036 0.9642 0.0905
-2.000 -0.1768 0.01373 0.00558 -0.0069 0.9584 0.1018
-1.750 -0.1408 0.01300 0.00509 -0.0087 0.9491 0.1433
-1.500 -0.1239 0.01033 0.00490 -0.0068 0.9415 0.7043
-1.250 -0.0904 0.01004 0.00505 -0.0065 0.9322 0.8088
-0.750 -0.0115 0.01018 0.00528 -0.0086 0.9141 0.9077
-0.500 0.0376 0.01031 0.00536 -0.0117 0.9056 0.9282
-0.250 0.0967 0.01060 0.00560 -0.0166 0.8927 0.9441
0.000 0.1495 0.01066 0.00557 -0.0210 0.8769 0.9532
0.250 0.1924 0.01062 0.00544 -0.0237 0.8571 0.9603
0.500 0.2281 0.01058 0.00533 -0.0251 0.8334 0.9695
0.750 0.2711 0.01048 0.00512 -0.0280 0.8075 0.9755
1.000 0.3096 0.01045 0.00493 -0.0299 0.7804 0.9835
1.250 0.3487 0.01048 0.00477 -0.0321 0.7521 0.9901
1.500 0.3903 0.01044 0.00462 -0.0350 0.7209 0.9968
1.750 0.4221 0.01044 0.00450 -0.0360 0.6933 1.0000
2.000 0.4443 0.01047 0.00441 -0.0351 0.6684 1.0000
2.250 0.4669 0.01052 0.00435 -0.0342 0.6451 1.0000
2.500 0.4897 0.01059 0.00433 -0.0333 0.6222 1.0000
2.750 0.5127 0.01067 0.00435 -0.0325 0.5998 1.0000
3.000 0.5357 0.01078 0.00438 -0.0316 0.5777 1.0000
3.250 0.5586 0.01091 0.00442 -0.0307 0.5556 1.0000
3.500 0.5813 0.01106 0.00449 -0.0298 0.5331 1.0000
3.750 0.6039 0.01120 0.00459 -0.0288 0.5090 1.0000
4.000 0.6257 0.01138 0.00471 -0.0276 0.4836 1.0000
4.250 0.6471 0.01159 0.00483 -0.0264 0.4555 1.0000
4.500 0.6675 0.01184 0.00497 -0.0250 0.4237 1.0000
4.750 0.6874 0.01213 0.00515 -0.0235 0.3866 1.0000
5.000 0.7063 0.01251 0.00538 -0.0219 0.3451 1.0000
5.250 0.7242 0.01299 0.00565 -0.0202 0.3041 1.0000
5.500 0.7420 0.01352 0.00600 -0.0184 0.2698 1.0000
5.750 0.7599 0.01407 0.00639 -0.0167 0.2444 1.0000
6.000 0.7779 0.01460 0.00680 -0.0151 0.2225 1.0000
6.250 0.7966 0.01506 0.00718 -0.0135 0.2040 1.0000
6.500 0.8157 0.01550 0.00758 -0.0120 0.1884 1.0000
6.750 0.8347 0.01597 0.00801 -0.0105 0.1761 1.0000
7.000 0.8537 0.01643 0.00846 -0.0090 0.1647 1.0000
7.250 0.8728 0.01688 0.00890 -0.0075 0.1530 1.0000
7.500 0.8917 0.01733 0.00936 -0.0060 0.1405 1.0000
7.750 0.9098 0.01783 0.00984 -0.0044 0.1274 1.0000
8.000 0.9275 0.01837 0.01036 -0.0028 0.1114 1.0000
8.500 0.9590 0.01986 0.01170 0.0011 0.0741 1.0000
8.750 0.9719 0.02087 0.01263 0.0034 0.0646 1.0000
9.000 0.9855 0.02181 0.01353 0.0056 0.0584 1.0000
9.250 0.9993 0.02275 0.01446 0.0076 0.0539 1.0000
9.500 1.0134 0.02371 0.01547 0.0096 0.0504 1.0000
9.750 1.0270 0.02478 0.01656 0.0117 0.0478 1.0000
10.000 1.0406 0.02587 0.01762 0.0135 0.0457 1.0000
10.250 1.0551 0.02704 0.01888 0.0154 0.0437 1.0000
10.500 1.0700 0.02822 0.02004 0.0169 0.0421 1.0000
10.750 1.0857 0.02961 0.02149 0.0184 0.0407 1.0000
11.000 1.1015 0.03097 0.02297 0.0199 0.0394 1.0000
11.250 1.1192 0.03238 0.02436 0.0209 0.0383 1.0000
11.500 1.1344 0.03403 0.02614 0.0222 0.0373 1.0000
11.750 1.1437 0.03562 0.02796 0.0243 0.0364 1.0000
12.000 1.1548 0.03719 0.02966 0.0260 0.0356 1.0000
12.250 1.1698 0.03881 0.03131 0.0271 0.0348 1.0000
12.500 1.1872 0.04098 0.03353 0.0276 0.0343 1.0000
12.750 1.1852 0.04309 0.03594 0.0306 0.0341 1.0000
13.000 1.1811 0.04544 0.03858 0.0332 0.0340 1.0000
13.250 1.1746 0.04806 0.04149 0.0354 0.0339 1.0000
13.500 1.1657 0.05099 0.04469 0.0372 0.0338 1.0000
13.750 1.1543 0.05428 0.04824 0.0383 0.0338 1.0000
14.000 1.1409 0.05799 0.05219 0.0387 0.0338 1.0000
14.250 1.1257 0.06216 0.05660 0.0384 0.0339 1.0000
14.500 1.1091 0.06682 0.06148 0.0372 0.0339 1.0000
14.750 1.0914 0.07198 0.06683 0.0354 0.0340 1.0000
15.000 1.0735 0.07755 0.07259 0.0329 0.0342 1.0000
15.250 1.0558 0.08347 0.07866 0.0299 0.0343 1.0000
15.500 0.8737 0.12534 0.12134 -0.0011 0.0377 1.0000
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Polar data table (+)
Polar graphs
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