NPL 9627 AIRFOIL (npl9627-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9627 AIRFOIL (npl9627-il) Reynolds number: 50,000 Max Cl/Cd: 28.84 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9627-il-50000.txt Download as CSV file: xf-npl9627-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NPL 9627 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6620 0.08568 0.07850 -0.0268 1.0000 0.1473
-9.250 -0.6348 0.08189 0.07473 -0.0250 1.0000 0.1435
-9.000 -0.7153 0.07072 0.06326 -0.0307 1.0000 0.1324
-8.750 -0.7125 0.06594 0.05843 -0.0304 1.0000 0.1303
-8.500 -0.7201 0.06080 0.05308 -0.0298 1.0000 0.1278
-8.250 -0.7296 0.05553 0.04741 -0.0286 1.0000 0.1253
-8.000 -0.7328 0.05074 0.04214 -0.0269 1.0000 0.1235
-7.750 -0.7280 0.04679 0.03773 -0.0250 1.0000 0.1234
-7.500 -0.7167 0.04373 0.03436 -0.0233 1.0000 0.1258
-7.250 -0.7046 0.04083 0.03104 -0.0214 1.0000 0.1292
-7.000 -0.6917 0.03812 0.02771 -0.0192 1.0000 0.1328
-6.750 -0.6713 0.03588 0.02559 -0.0181 1.0000 0.1395
-6.500 -0.6540 0.03388 0.02310 -0.0162 1.0000 0.1473
-6.250 -0.6322 0.03193 0.02130 -0.0151 1.0000 0.1564
-6.000 -0.6104 0.03004 0.01932 -0.0137 1.0000 0.1670
-5.750 -0.5882 0.02837 0.01765 -0.0124 1.0000 0.1820
-5.500 -0.5663 0.02675 0.01617 -0.0109 1.0000 0.2039
-5.250 -0.5474 0.02506 0.01487 -0.0089 1.0000 0.2482
-5.000 -0.5383 0.02357 0.01415 -0.0050 1.0000 0.3506
-4.750 -0.5275 0.02297 0.01387 -0.0012 1.0000 0.4294
-4.500 -0.5125 0.02251 0.01360 0.0019 1.0000 0.4841
-4.250 -0.4983 0.02227 0.01363 0.0055 1.0000 0.5382
-4.000 -0.4853 0.02224 0.01387 0.0098 1.0000 0.5940
-3.750 -0.4690 0.02211 0.01394 0.0136 1.0000 0.6402
-3.500 -0.4498 0.02181 0.01370 0.0164 1.0000 0.6798
-3.250 -0.4310 0.02155 0.01349 0.0192 1.0000 0.7202
-3.000 -0.4111 0.02146 0.01344 0.0222 1.0000 0.7613
-2.750 -0.3874 0.02155 0.01356 0.0248 1.0000 0.8058
-2.500 -0.3491 0.02193 0.01385 0.0250 1.0000 0.8559
-2.250 -0.2629 0.02268 0.01429 0.0164 1.0000 0.9113
-2.000 -0.1186 0.02279 0.01388 -0.0046 1.0000 0.9624
-1.750 -0.0026 0.02176 0.01249 -0.0232 1.0000 1.0000
-1.500 -0.0196 0.02123 0.01197 -0.0190 1.0000 1.0000
-1.250 -0.0388 0.02098 0.01171 -0.0138 1.0000 1.0000
-1.000 -0.0567 0.02094 0.01163 -0.0085 1.0000 1.0000
-0.750 -0.0701 0.02105 0.01168 -0.0038 1.0000 1.0000
-0.500 -0.0775 0.02128 0.01181 0.0001 1.0000 1.0000
-0.250 -0.0797 0.02160 0.01204 0.0031 1.0000 1.0000
0.000 -0.0774 0.02202 0.01236 0.0054 1.0000 1.0000
0.250 -0.0712 0.02252 0.01277 0.0070 1.0000 1.0000
0.500 -0.0256 0.02337 0.01354 0.0016 0.9878 1.0000
0.750 0.0401 0.02431 0.01443 -0.0071 0.9682 1.0000
1.000 0.0991 0.02505 0.01515 -0.0143 0.9475 1.0000
1.250 0.1546 0.02564 0.01575 -0.0204 0.9261 1.0000
1.500 0.2152 0.02609 0.01625 -0.0270 0.9052 1.0000
1.750 0.2847 0.02628 0.01654 -0.0347 0.8849 1.0000
2.000 0.3328 0.02645 0.01679 -0.0382 0.8622 1.0000
2.250 0.3770 0.02656 0.01698 -0.0407 0.8398 1.0000
2.500 0.4218 0.02652 0.01703 -0.0428 0.8182 1.0000
2.750 0.4628 0.02640 0.01700 -0.0439 0.7972 1.0000
3.000 0.4944 0.02645 0.01710 -0.0433 0.7751 1.0000
3.250 0.5182 0.02669 0.01742 -0.0417 0.7511 1.0000
3.500 0.5470 0.02663 0.01740 -0.0402 0.7280 1.0000
3.750 0.5759 0.02642 0.01720 -0.0382 0.7048 1.0000
4.000 0.5958 0.02647 0.01729 -0.0352 0.6760 1.0000
4.250 0.6190 0.02602 0.01678 -0.0318 0.6448 1.0000
4.500 0.6414 0.02547 0.01612 -0.0282 0.6112 1.0000
4.750 0.6630 0.02514 0.01567 -0.0249 0.5780 1.0000
5.000 0.6837 0.02515 0.01561 -0.0222 0.5463 1.0000
5.250 0.7033 0.02527 0.01566 -0.0195 0.5116 1.0000
5.500 0.7223 0.02537 0.01562 -0.0166 0.4722 1.0000
5.750 0.7391 0.02563 0.01568 -0.0135 0.4244 1.0000
6.000 0.7552 0.02625 0.01589 -0.0103 0.3699 1.0000
6.250 0.7711 0.02738 0.01667 -0.0077 0.3214 1.0000
6.500 0.7906 0.02881 0.01791 -0.0060 0.2892 1.0000
6.750 0.8135 0.03026 0.01909 -0.0049 0.2679 1.0000
7.000 0.8355 0.03176 0.02054 -0.0038 0.2512 1.0000
7.250 0.8555 0.03345 0.02245 -0.0025 0.2383 1.0000
7.500 0.8755 0.03529 0.02443 -0.0014 0.2276 1.0000
7.750 0.8993 0.03699 0.02598 -0.0008 0.2177 1.0000
8.000 0.9128 0.03918 0.02865 0.0010 0.2095 1.0000
8.250 0.9358 0.04106 0.03040 0.0016 0.2013 1.0000
8.500 0.9434 0.04380 0.03371 0.0037 0.1953 1.0000
8.750 0.9617 0.04588 0.03586 0.0047 0.1885 1.0000
9.000 0.9715 0.04894 0.03918 0.0062 0.1841 1.0000
9.250 0.9685 0.05274 0.04350 0.0084 0.1811 1.0000
9.500 0.9624 0.05690 0.04806 0.0103 0.1790 1.0000
9.750 0.9488 0.06165 0.05316 0.0120 0.1781 1.0000
10.000 0.9187 0.06766 0.05947 0.0132 0.1793 1.0000
10.250 0.8757 0.07467 0.06661 0.0135 0.1821 1.0000
10.500 0.8432 0.08236 0.07435 0.0112 0.1845 1.0000
10.750 0.8256 0.08986 0.08188 0.0083 0.1861 1.0000
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Polar data table (+)
Polar graphs
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