NPL 9626 AIRFOIL (npl9626-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9626 AIRFOIL (npl9626-il) Reynolds number: 200,000 Max Cl/Cd: 53.3 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9626-il-200000.txt Download as CSV file: xf-npl9626-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9626 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5063 0.08972 0.08619 -0.0209 1.0000 0.0750
-10.250 -0.7460 0.04987 0.04549 -0.0415 1.0000 0.0443
-10.000 -0.8595 0.05145 0.04615 -0.0317 1.0000 0.0385
-9.750 -0.8526 0.04792 0.04254 -0.0305 1.0000 0.0378
-9.500 -0.8525 0.04396 0.03829 -0.0283 1.0000 0.0368
-9.250 -0.8555 0.03914 0.03292 -0.0253 1.0000 0.0355
-9.000 -0.8514 0.03515 0.02838 -0.0224 1.0000 0.0350
-8.750 -0.8382 0.03271 0.02565 -0.0205 1.0000 0.0354
-8.500 -0.8227 0.03063 0.02331 -0.0187 1.0000 0.0361
-8.250 -0.8062 0.02867 0.02107 -0.0169 1.0000 0.0371
-8.000 -0.7889 0.02692 0.01896 -0.0150 1.0000 0.0384
-7.750 -0.7696 0.02518 0.01710 -0.0136 1.0000 0.0398
-7.500 -0.7496 0.02420 0.01612 -0.0124 1.0000 0.0415
-7.250 -0.7295 0.02324 0.01502 -0.0110 1.0000 0.0437
-7.000 -0.7092 0.02200 0.01366 -0.0096 1.0000 0.0456
-6.750 -0.6894 0.02112 0.01286 -0.0083 1.0000 0.0480
-6.500 -0.6694 0.02048 0.01212 -0.0068 1.0000 0.0512
-6.250 -0.6504 0.01943 0.01113 -0.0053 1.0000 0.0543
-6.000 -0.6310 0.01882 0.01052 -0.0038 1.0000 0.0581
-5.750 -0.6123 0.01799 0.00968 -0.0022 1.0000 0.0619
-5.500 -0.5938 0.01732 0.00907 -0.0006 1.0000 0.0661
-5.250 -0.5741 0.01686 0.00852 0.0009 1.0000 0.0702
-5.000 -0.5569 0.01602 0.00781 0.0026 1.0000 0.0758
-4.750 -0.5377 0.01550 0.00727 0.0041 1.0000 0.0825
-4.500 -0.5187 0.01491 0.00674 0.0055 1.0000 0.0927
-4.250 -0.5000 0.01415 0.00614 0.0069 1.0000 0.1138
-4.000 -0.4833 0.01265 0.00554 0.0080 1.0000 0.2592
-3.750 -0.4636 0.01201 0.00540 0.0089 1.0000 0.3750
-3.500 -0.4337 0.01166 0.00530 0.0081 0.9975 0.4382
-3.250 -0.3924 0.01134 0.00522 0.0051 0.9914 0.4997
-3.000 -0.3516 0.01104 0.00515 0.0023 0.9848 0.5597
-2.750 -0.3138 0.01074 0.00513 0.0003 0.9769 0.6246
-2.500 -0.2724 0.01051 0.00515 -0.0021 0.9709 0.6885
-2.250 -0.2367 0.01032 0.00516 -0.0032 0.9612 0.7409
-2.000 -0.1959 0.01020 0.00517 -0.0052 0.9545 0.7846
-1.750 -0.1603 0.01011 0.00515 -0.0060 0.9445 0.8176
-1.500 -0.1257 0.01006 0.00513 -0.0065 0.9337 0.8436
-1.250 -0.0888 0.01002 0.00509 -0.0075 0.9239 0.8654
-1.000 -0.0570 0.01000 0.00507 -0.0073 0.9095 0.8853
-0.750 -0.0250 0.01002 0.00505 -0.0072 0.8933 0.9026
-0.500 0.0087 0.01006 0.00504 -0.0073 0.8756 0.9171
-0.250 0.0431 0.01011 0.00503 -0.0078 0.8561 0.9299
0.000 0.0770 0.01019 0.00502 -0.0083 0.8324 0.9424
0.250 0.1181 0.01028 0.00499 -0.0103 0.8077 0.9504
0.500 0.1578 0.01038 0.00496 -0.0123 0.7796 0.9592
0.750 0.1986 0.01049 0.00493 -0.0146 0.7506 0.9677
1.000 0.2405 0.01061 0.00489 -0.0173 0.7211 0.9753
1.250 0.2812 0.01074 0.00488 -0.0198 0.6922 0.9841
1.500 0.3248 0.01085 0.00484 -0.0231 0.6654 0.9910
1.750 0.3678 0.01093 0.00479 -0.0264 0.6380 0.9974
2.000 0.3993 0.01101 0.00474 -0.0274 0.6146 1.0000
2.250 0.4228 0.01107 0.00471 -0.0268 0.5934 1.0000
2.500 0.4465 0.01114 0.00471 -0.0262 0.5738 1.0000
2.750 0.4701 0.01123 0.00471 -0.0256 0.5549 1.0000
3.000 0.4935 0.01132 0.00473 -0.0248 0.5358 1.0000
3.250 0.5161 0.01145 0.00474 -0.0239 0.5142 1.0000
3.500 0.5386 0.01153 0.00479 -0.0230 0.4918 1.0000
3.750 0.5614 0.01166 0.00487 -0.0221 0.4733 1.0000
4.000 0.5842 0.01179 0.00499 -0.0212 0.4560 1.0000
4.250 0.6067 0.01193 0.00511 -0.0202 0.4372 1.0000
4.500 0.6286 0.01210 0.00523 -0.0191 0.4150 1.0000
4.750 0.6501 0.01228 0.00537 -0.0179 0.3852 1.0000
5.000 0.6700 0.01257 0.00552 -0.0164 0.3311 1.0000
5.250 0.6777 0.01429 0.00614 -0.0136 0.1440 1.0000
5.500 0.6932 0.01531 0.00691 -0.0117 0.1086 1.0000
5.750 0.7110 0.01603 0.00756 -0.0099 0.0974 1.0000
6.000 0.7280 0.01680 0.00826 -0.0081 0.0900 1.0000
6.250 0.7468 0.01740 0.00890 -0.0065 0.0848 1.0000
6.500 0.7651 0.01806 0.00955 -0.0049 0.0801 1.0000
6.750 0.7813 0.01904 0.01047 -0.0031 0.0764 1.0000
7.000 0.8011 0.01970 0.01118 -0.0016 0.0732 1.0000
7.250 0.8205 0.02047 0.01196 -0.0002 0.0702 1.0000
7.500 0.8392 0.02160 0.01300 0.0011 0.0674 1.0000
7.750 0.8600 0.02261 0.01407 0.0023 0.0650 1.0000
8.000 0.8811 0.02343 0.01497 0.0034 0.0622 1.0000
8.250 0.9022 0.02436 0.01588 0.0043 0.0596 1.0000
8.500 0.9243 0.02612 0.01757 0.0049 0.0572 1.0000
8.750 0.9444 0.02686 0.01852 0.0061 0.0550 1.0000
9.000 0.9650 0.02785 0.01960 0.0071 0.0526 1.0000
9.250 0.9859 0.02908 0.02087 0.0079 0.0509 1.0000
9.500 1.0088 0.03144 0.02320 0.0080 0.0493 1.0000
9.750 1.0252 0.03299 0.02506 0.0096 0.0482 1.0000
10.000 1.0404 0.03462 0.02700 0.0112 0.0468 1.0000
10.250 1.0550 0.03639 0.02901 0.0127 0.0455 1.0000
10.500 1.0702 0.03801 0.03077 0.0140 0.0441 1.0000
10.750 1.0877 0.03960 0.03238 0.0147 0.0430 1.0000
11.000 1.1015 0.04253 0.03540 0.0155 0.0420 1.0000
11.250 1.1050 0.04614 0.03932 0.0175 0.0416 1.0000
11.500 1.1036 0.04875 0.04228 0.0201 0.0414 1.0000
11.750 1.0987 0.05175 0.04559 0.0226 0.0413 1.0000
12.000 1.0889 0.05487 0.04899 0.0254 0.0413 1.0000
12.250 1.0761 0.05818 0.05252 0.0280 0.0414 1.0000
12.500 1.0632 0.06201 0.05654 0.0296 0.0415 1.0000
12.750 1.0539 0.06605 0.06075 0.0304 0.0418 1.0000
13.000 0.9218 0.08131 0.07699 0.0217 0.0452 1.0000
13.250 0.8638 0.09556 0.09146 0.0115 0.0469 1.0000
13.500 0.8396 0.10491 0.10086 0.0063 0.0481 1.0000
13.750 0.8631 0.10480 0.10071 0.0097 0.0495 1.0000
14.000 0.5717 0.13801 0.13428 0.0020 0.0776 1.0000
14.250 0.5526 0.14277 0.13902 -0.0006 0.0768 1.0000
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