NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: NPL 9510 AIRFOIL (npl9510-il) Reynolds number: 50,000 Max Cl/Cd: 17 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-npl9510-il-50000-n5.txt Download as CSV file: xf-npl9510-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9510 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.7586 0.10159 0.09304 -0.0315 1.0000 0.0720
-12.500 -0.8055 0.08829 0.07961 -0.0397 1.0000 0.0711
-12.250 -0.8441 0.07848 0.06961 -0.0456 1.0000 0.0704
-12.000 -0.8706 0.07156 0.06249 -0.0493 1.0000 0.0704
-11.750 -0.8893 0.06621 0.05692 -0.0514 1.0000 0.0710
-11.500 -0.9031 0.06177 0.05224 -0.0526 1.0000 0.0718
-11.250 -0.9135 0.05796 0.04818 -0.0530 1.0000 0.0728
-11.000 -0.9210 0.05460 0.04450 -0.0527 1.0000 0.0740
-10.750 -0.9148 0.05208 0.04186 -0.0521 1.0000 0.0757
-10.500 -0.9050 0.05022 0.03998 -0.0514 1.0000 0.0783
-10.250 -0.8972 0.04811 0.03773 -0.0508 1.0000 0.0815
-10.000 -0.8890 0.04582 0.03511 -0.0500 1.0000 0.0852
-9.750 -0.8746 0.04434 0.03368 -0.0487 1.0000 0.0890
-9.500 -0.8623 0.04273 0.03197 -0.0476 1.0000 0.0941
-9.250 -0.8488 0.04116 0.03029 -0.0463 1.0000 0.0999
-9.000 -0.8359 0.03975 0.02888 -0.0451 1.0000 0.1064
-8.750 -0.8230 0.03829 0.02738 -0.0438 1.0000 0.1143
-8.500 -0.8100 0.03684 0.02582 -0.0426 1.0000 0.1242
-8.250 -0.7976 0.03540 0.02448 -0.0416 1.0000 0.1349
-8.000 -0.7846 0.03391 0.02304 -0.0407 1.0000 0.1483
-7.750 -0.7709 0.03240 0.02158 -0.0401 1.0000 0.1650
-7.500 -0.7557 0.03089 0.02010 -0.0397 1.0000 0.1852
-7.250 -0.7398 0.02936 0.01879 -0.0396 1.0000 0.2083
-7.000 -0.7219 0.02791 0.01756 -0.0398 1.0000 0.2385
-6.750 -0.7023 0.02669 0.01665 -0.0399 1.0000 0.2780
-6.500 -0.6818 0.02607 0.01637 -0.0393 1.0000 0.3239
-6.250 -0.6606 0.02609 0.01660 -0.0378 1.0000 0.3674
-6.000 -0.6382 0.02629 0.01680 -0.0364 1.0000 0.4042
-5.750 -0.6157 0.02661 0.01705 -0.0349 1.0000 0.4324
-5.500 -0.5918 0.02667 0.01693 -0.0343 1.0000 0.4578
-5.250 -0.5698 0.02704 0.01720 -0.0325 1.0000 0.4761
-5.000 -0.5476 0.02731 0.01736 -0.0310 1.0000 0.4930
-4.750 -0.5252 0.02751 0.01743 -0.0296 1.0000 0.5090
-4.500 -0.5024 0.02760 0.01741 -0.0285 1.0000 0.5243
-4.250 -0.4814 0.02783 0.01759 -0.0266 1.0000 0.5366
-4.000 -0.4609 0.02804 0.01774 -0.0245 1.0000 0.5480
-3.750 -0.4388 0.02809 0.01772 -0.0232 1.0000 0.5615
-3.500 -0.4159 0.02807 0.01762 -0.0223 1.0000 0.5757
-3.250 -0.3968 0.02826 0.01781 -0.0198 1.0000 0.5856
-3.000 -0.3737 0.02808 0.01756 -0.0191 1.0000 0.5962
-2.750 -0.3500 0.02783 0.01726 -0.0186 1.0000 0.6051
-2.500 -0.3252 0.02751 0.01689 -0.0185 1.0000 0.6130
-2.250 -0.3017 0.02727 0.01662 -0.0179 1.0000 0.6199
-2.000 -0.2737 0.02686 0.01615 -0.0189 1.0000 0.6283
-1.750 -0.2512 0.02668 0.01598 -0.0179 1.0000 0.6338
-1.500 -0.2236 0.02637 0.01563 -0.0187 1.0000 0.6415
-1.250 -0.1983 0.02613 0.01541 -0.0187 1.0000 0.6474
-1.000 -0.1743 0.02595 0.01526 -0.0183 1.0000 0.6532
-0.750 -0.1445 0.02568 0.01498 -0.0197 1.0000 0.6609
-0.500 -0.1210 0.02555 0.01493 -0.0191 1.0000 0.6656
-0.250 -0.0956 0.02543 0.01487 -0.0190 1.0000 0.6716
0.000 -0.0651 0.02527 0.01475 -0.0206 1.0000 0.6788
0.250 -0.0417 0.02521 0.01481 -0.0200 1.0000 0.6834
0.500 -0.0157 0.02515 0.01487 -0.0201 1.0000 0.6893
0.750 0.0144 0.02511 0.01492 -0.0215 1.0000 0.6962
1.000 0.0382 0.02511 0.01509 -0.0211 1.0000 0.7009
1.250 0.0645 0.02514 0.01528 -0.0214 1.0000 0.7069
1.500 0.0935 0.02521 0.01552 -0.0225 1.0000 0.7135
1.750 0.1175 0.02530 0.01584 -0.0222 1.0000 0.7185
2.000 0.1441 0.02544 0.01622 -0.0226 1.0000 0.7248
2.250 0.3113 0.02543 0.01337 -0.0399 0.1727 0.7308
2.500 0.3340 0.02633 0.01402 -0.0391 0.1363 0.7359
2.750 0.3610 0.02709 0.01472 -0.0391 0.1194 0.7422
3.000 0.3885 0.02783 0.01544 -0.0391 0.1080 0.7481
3.250 0.4166 0.02856 0.01625 -0.0389 0.1004 0.7539
3.500 0.4509 0.02949 0.01722 -0.0400 0.0940 0.7607
3.750 0.4819 0.03030 0.01815 -0.0401 0.0878 0.7665
4.000 0.5142 0.03151 0.01932 -0.0407 0.0841 0.7732
4.250 0.5466 0.03278 0.02082 -0.0412 0.0809 0.7799
4.500 0.5749 0.03399 0.02226 -0.0409 0.0770 0.7865
5.000 0.6303 0.03708 0.02566 -0.0408 0.0725 0.8008
5.250 0.6571 0.03908 0.02797 -0.0407 0.0708 0.8087
5.500 0.6803 0.04102 0.03047 -0.0396 0.0685 0.8159
5.750 0.7032 0.04323 0.03311 -0.0389 0.0665 0.8243
6.000 0.7230 0.04567 0.03599 -0.0377 0.0658 0.8323
6.500 0.7575 0.05113 0.04231 -0.0353 0.0645 0.8504
6.750 0.7725 0.05374 0.04526 -0.0342 0.0633 0.8606
7.000 0.7876 0.05615 0.04784 -0.0332 0.0619 0.8725
7.250 0.7994 0.05904 0.05093 -0.0320 0.0610 0.8858
7.500 0.8058 0.06254 0.05489 -0.0303 0.0609 0.9013
7.750 0.8126 0.06614 0.05883 -0.0291 0.0610 0.9249
8.250 0.7970 0.07785 0.07164 -0.0292 0.0641 1.0000
8.500 0.7874 0.08371 0.07772 -0.0306 0.0656 1.0000
8.750 0.7759 0.08914 0.08326 -0.0323 0.0669 1.0000
9.000 0.7660 0.09476 0.08893 -0.0349 0.0681 1.0000
9.250 0.7596 0.10056 0.09474 -0.0384 0.0692 1.0000
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