NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Reynolds number: 100,000 Max Cl/Cd: 28.84 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nplx-il-100000.txt Download as CSV file: xf-nplx-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NPL AIRFOIL FROM ARC CP 1372
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5744 0.10093 0.09555 -0.0299 1.0000 0.1239
-9.250 -0.5453 0.09927 0.09384 -0.0251 1.0000 0.1278
-9.000 -0.5487 0.09546 0.09009 -0.0265 1.0000 0.1333
-8.750 -0.6082 0.08785 0.08262 -0.0369 1.0000 0.1369
-8.500 -0.5693 0.08593 0.08071 -0.0307 1.0000 0.1419
-8.250 -0.5710 0.08231 0.07714 -0.0312 1.0000 0.1468
-8.000 -0.6153 0.07653 0.07145 -0.0356 1.0000 0.1500
-7.750 -0.6791 0.07351 0.06822 -0.0372 1.0000 0.1525
-7.500 -0.6412 0.06872 0.06368 -0.0351 1.0000 0.1587
-7.250 -0.6560 0.06549 0.06038 -0.0346 1.0000 0.1650
-7.000 -0.6624 0.06179 0.05667 -0.0335 1.0000 0.1737
-6.500 -0.6763 0.04710 0.04039 -0.0330 1.0000 0.0962
-6.250 -0.6647 0.04020 0.03208 -0.0295 1.0000 0.0659
-6.000 -0.6495 0.03665 0.02832 -0.0282 1.0000 0.0650
-5.750 -0.6330 0.03380 0.02512 -0.0266 1.0000 0.0649
-5.500 -0.6145 0.03145 0.02239 -0.0250 1.0000 0.0656
-5.250 -0.5960 0.02887 0.01964 -0.0238 1.0000 0.0684
-5.000 -0.5763 0.02757 0.01835 -0.0227 1.0000 0.0738
-4.750 -0.5563 0.02600 0.01651 -0.0213 1.0000 0.0810
-4.500 -0.5356 0.02464 0.01516 -0.0202 1.0000 0.0873
-4.250 -0.5139 0.02335 0.01367 -0.0188 1.0000 0.0942
-4.000 -0.4931 0.02204 0.01247 -0.0176 1.0000 0.1021
-3.750 -0.4720 0.02092 0.01134 -0.0162 1.0000 0.1100
-3.500 -0.4516 0.02001 0.01052 -0.0149 1.0000 0.1201
-3.250 -0.4321 0.01908 0.00977 -0.0136 1.0000 0.1319
-3.000 -0.4123 0.01826 0.00906 -0.0123 1.0000 0.1495
-2.750 -0.3917 0.01719 0.00817 -0.0115 1.0000 0.1835
-2.500 -0.3804 0.01534 0.00841 -0.0088 1.0000 0.5951
-2.250 -0.3666 0.01620 0.00928 -0.0046 1.0000 0.6514
-2.000 -0.3527 0.01679 0.00993 -0.0006 1.0000 0.6788
-1.750 -0.3372 0.01720 0.01032 0.0025 1.0000 0.7019
-1.500 -0.3232 0.01755 0.01068 0.0061 1.0000 0.7211
-1.250 -0.3095 0.01782 0.01096 0.0096 1.0000 0.7401
-1.000 -0.2955 0.01801 0.01115 0.0128 1.0000 0.7579
-0.750 -0.2814 0.01813 0.01127 0.0159 1.0000 0.7745
-0.500 -0.2668 0.01818 0.01132 0.0187 1.0000 0.7892
-0.250 -0.2506 0.01816 0.01128 0.0209 1.0000 0.8018
0.000 -0.2298 0.01809 0.01116 0.0216 1.0000 0.8120
0.250 -0.2104 0.01800 0.01107 0.0227 1.0000 0.8188
0.500 -0.1861 0.01794 0.01095 0.0223 1.0000 0.8251
0.750 -0.1647 0.01787 0.01088 0.0227 1.0000 0.8304
1.000 -0.1429 0.01787 0.01087 0.0230 1.0000 0.8373
1.250 -0.1205 0.01789 0.01089 0.0230 1.0000 0.8444
1.500 -0.0872 0.01817 0.01120 0.0210 0.9949 0.8512
1.750 -0.0348 0.01868 0.01172 0.0154 0.9822 0.8582
2.000 0.0090 0.01898 0.01209 0.0118 0.9710 0.8659
2.250 0.0519 0.01920 0.01239 0.0083 0.9601 0.8749
2.500 0.0917 0.01931 0.01259 0.0056 0.9479 0.8844
2.750 0.1448 0.01930 0.01272 0.0010 0.9317 0.8929
3.000 0.2082 0.01872 0.01229 -0.0043 0.9053 0.9011
3.250 0.2821 0.01741 0.01119 -0.0100 0.8757 0.9071
3.500 0.3624 0.01535 0.00932 -0.0150 0.8320 0.9114
3.750 0.4066 0.01423 0.00827 -0.0149 0.7650 0.9202
4.000 0.4286 0.01486 0.00721 -0.0106 0.3953 0.9308
4.250 0.4406 0.01718 0.00796 -0.0085 0.1645 0.9461
4.500 0.4743 0.01839 0.00893 -0.0099 0.1372 0.9608
4.750 0.5161 0.01962 0.01003 -0.0131 0.1216 0.9749
5.000 0.5623 0.02125 0.01139 -0.0172 0.1116 0.9884
5.250 0.5967 0.02223 0.01247 -0.0190 0.1073 1.0000
5.500 0.6151 0.02315 0.01341 -0.0181 0.1044 1.0000
5.750 0.6429 0.02439 0.01462 -0.0187 0.1005 1.0000
6.000 0.6734 0.02654 0.01667 -0.0199 0.0968 1.0000
6.250 0.7014 0.02791 0.01830 -0.0200 0.0953 1.0000
6.500 0.7287 0.02968 0.02032 -0.0199 0.0946 1.0000
6.750 0.7544 0.03176 0.02267 -0.0196 0.0944 1.0000
7.000 0.7780 0.03401 0.02522 -0.0190 0.0944 1.0000
7.250 0.7991 0.03629 0.02786 -0.0180 0.0938 1.0000
7.500 0.8181 0.03887 0.03079 -0.0168 0.0936 1.0000
7.750 0.8363 0.04234 0.03451 -0.0159 0.0954 1.0000
8.000 0.8437 0.04734 0.04044 -0.0128 0.1080 1.0000
8.500 0.7784 0.07259 0.06784 -0.0143 0.2213 1.0000
8.750 0.7466 0.07690 0.07216 -0.0144 0.2109 1.0000
9.000 0.7965 0.08005 0.07523 -0.0127 0.2021 1.0000
9.250 0.7172 0.08580 0.08098 -0.0172 0.1954 1.0000
9.500 0.7728 0.08730 0.08249 -0.0120 0.1867 1.0000
9.750 0.7021 0.09499 0.09006 -0.0215 0.1804 1.0000
10.000 0.7696 0.09495 0.09010 -0.0122 0.1718 1.0000
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Polar data table (+)
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