NPL 9510 AIRFOIL (npl9510-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NPL 9510 AIRFOIL (npl9510-il) Reynolds number: 50,000 Max Cl/Cd: 15.53 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-npl9510-il-50000.txt Download as CSV file: xf-npl9510-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5601 0.12253 0.11403 -0.0012 1.0000 0.3186
-10.250 -0.8266 0.07001 0.06188 -0.0453 1.0000 0.1477
-10.000 -0.8999 0.06004 0.05133 -0.0512 1.0000 0.1411
-9.750 -0.8911 0.05666 0.04789 -0.0506 1.0000 0.1440
-9.500 -0.8886 0.05295 0.04394 -0.0506 1.0000 0.1473
-9.250 -0.8863 0.04890 0.03944 -0.0511 1.0000 0.1512
-9.000 -0.8784 0.04492 0.03492 -0.0516 1.0000 0.1557
-8.750 -0.8595 0.04259 0.03268 -0.0505 1.0000 0.1638
-8.500 -0.8437 0.03956 0.02931 -0.0505 1.0000 0.1731
-8.250 -0.8252 0.03707 0.02653 -0.0502 1.0000 0.1857
-8.000 -0.8055 0.03483 0.02431 -0.0494 1.0000 0.2021
-7.750 -0.7858 0.03296 0.02275 -0.0479 1.0000 0.2225
-7.500 -0.7662 0.03106 0.02094 -0.0470 1.0000 0.2510
-7.250 -0.7469 0.02974 0.01999 -0.0455 1.0000 0.2850
-7.000 -0.7271 0.02902 0.01963 -0.0437 1.0000 0.3248
-6.750 -0.7074 0.02942 0.02040 -0.0407 1.0000 0.3652
-6.500 -0.6885 0.03109 0.02232 -0.0357 1.0000 0.4009
-6.250 -0.6698 0.03331 0.02467 -0.0299 1.0000 0.4314
-6.000 -0.6511 0.03534 0.02670 -0.0244 1.0000 0.4602
-5.750 -0.6329 0.03769 0.02904 -0.0176 1.0000 0.4822
-5.500 -0.6154 0.03887 0.03014 -0.0130 1.0000 0.5089
-5.250 -0.5980 0.04032 0.03154 -0.0070 1.0000 0.5292
-5.000 -0.5819 0.04032 0.03141 -0.0042 1.0000 0.5574
-4.750 -0.5657 0.04104 0.03206 0.0011 1.0000 0.5765
-4.500 -0.5495 0.04138 0.03233 0.0059 1.0000 0.5964
-4.250 -0.5337 0.04136 0.03224 0.0100 1.0000 0.6168
-4.000 -0.5184 0.04096 0.03176 0.0133 1.0000 0.6375
-3.750 -0.5035 0.04033 0.03104 0.0159 1.0000 0.6577
-3.500 -0.4888 0.03960 0.03024 0.0183 1.0000 0.6771
-3.250 -0.4740 0.03883 0.02940 0.0206 1.0000 0.6957
-3.000 -0.4591 0.03808 0.02861 0.0234 1.0000 0.7133
-2.750 -0.4439 0.03726 0.02774 0.0261 1.0000 0.7303
-2.500 -0.4285 0.03635 0.02679 0.0281 1.0000 0.7463
-2.250 -0.4119 0.03539 0.02578 0.0297 1.0000 0.7601
-2.000 -0.3944 0.03437 0.02473 0.0313 1.0000 0.7716
-1.750 -0.3763 0.03333 0.02365 0.0318 1.0000 0.7823
-1.500 -0.3566 0.03239 0.02267 0.0317 1.0000 0.7925
-1.250 -0.3369 0.03144 0.02171 0.0325 1.0000 0.8014
-1.000 -0.3141 0.03061 0.02085 0.0314 1.0000 0.8104
-0.750 -0.2935 0.02974 0.01999 0.0321 1.0000 0.8186
-0.500 -0.2688 0.02903 0.01927 0.0308 1.0000 0.8267
-0.250 -0.2468 0.02827 0.01854 0.0311 1.0000 0.8345
0.000 -0.2207 0.02767 0.01797 0.0297 1.0000 0.8424
0.250 -0.1982 0.02701 0.01736 0.0298 1.0000 0.8500
0.500 -0.1716 0.02651 0.01691 0.0285 1.0000 0.8578
0.750 -0.1475 0.02597 0.01644 0.0282 1.0000 0.8654
1.000 -0.1201 0.02557 0.01613 0.0269 1.0000 0.8733
1.250 -0.0953 0.02513 0.01580 0.0264 1.0000 0.8812
1.500 -0.0677 0.02482 0.01562 0.0252 1.0000 0.8893
1.750 -0.0420 0.02449 0.01544 0.0244 1.0000 0.8978
2.000 -0.0151 0.02424 0.01536 0.0234 1.0000 0.9063
2.250 0.0121 0.02405 0.01538 0.0223 1.0000 0.9156
2.500 0.0383 0.02386 0.01542 0.0214 1.0000 0.9253
2.750 0.0657 0.02376 0.01560 0.0202 1.0000 0.9360
3.000 0.0938 0.02372 0.01592 0.0189 1.0000 0.9480
3.250 0.2999 0.02599 0.01513 0.0008 0.1930 0.9464
3.500 0.3605 0.02752 0.01665 -0.0045 0.1747 0.9545
3.750 0.4102 0.02906 0.01821 -0.0084 0.1623 0.9634
4.250 0.5049 0.03294 0.02281 -0.0155 0.1522 0.9830
4.500 0.5500 0.03541 0.02570 -0.0190 0.1506 0.9940
4.750 0.5767 0.03774 0.02847 -0.0194 0.1525 1.0000
5.000 0.5888 0.03971 0.03077 -0.0176 0.1537 1.0000
5.250 0.6070 0.04220 0.03365 -0.0170 0.1551 1.0000
5.500 0.6303 0.04547 0.03720 -0.0176 0.1582 1.0000
5.750 0.6538 0.04954 0.04202 -0.0184 0.1737 1.0000
7.000 0.5870 0.09202 0.08699 -0.0732 0.5137 1.0000
7.250 0.6290 0.09638 0.09136 -0.0725 0.4746 1.0000
7.500 0.6443 0.09972 0.09465 -0.0711 0.4377 1.0000
7.750 0.6612 0.10310 0.09801 -0.0697 0.4029 1.0000
8.000 0.6722 0.10619 0.10105 -0.0689 0.3718 1.0000
8.250 0.6784 0.11014 0.10493 -0.0690 0.3494 1.0000
8.500 0.6783 0.11361 0.10834 -0.0699 0.3288 1.0000
8.750 0.6860 0.11756 0.11224 -0.0705 0.3115 1.0000
9.000 0.6996 0.12193 0.11658 -0.0708 0.2966 1.0000
9.250 0.7266 0.12710 0.12174 -0.0697 0.2813 1.0000
9.500 0.7107 0.12947 0.12402 -0.0725 0.2680 1.0000
9.750 0.7073 0.13334 0.12781 -0.0745 0.2572 1.0000
10.000 0.7318 0.13869 0.13313 -0.0735 0.2459 1.0000
10.250 0.7217 0.14119 0.13557 -0.0762 0.2345 1.0000
10.500 0.7299 0.14582 0.14014 -0.0771 0.2268 1.0000
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Polar data table (+)
Polar graphs
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