NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: NPL AIRFOIL FROM ARC CP 1372 (nplx-il) Reynolds number: 100,000 Max Cl/Cd: 28.8 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nplx-il-100000-n5.txt Download as CSV file: xf-nplx-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5976 0.08964 0.08392 -0.0349 1.0000 0.0283
-10.000 -0.6197 0.08022 0.07449 -0.0409 1.0000 0.0275
-9.750 -0.6582 0.07039 0.06453 -0.0467 1.0000 0.0264
-9.500 -0.6825 0.06518 0.05921 -0.0485 1.0000 0.0264
-9.250 -0.7242 0.05918 0.05296 -0.0479 1.0000 0.0257
-9.000 -0.7301 0.05727 0.05100 -0.0462 1.0000 0.0262
-8.750 -0.7442 0.05350 0.04699 -0.0444 1.0000 0.0261
-8.500 -0.7475 0.05074 0.04405 -0.0426 1.0000 0.0265
-8.250 -0.7499 0.04756 0.04060 -0.0407 1.0000 0.0267
-8.000 -0.7486 0.04444 0.03718 -0.0388 1.0000 0.0270
-7.750 -0.7441 0.04136 0.03376 -0.0368 1.0000 0.0272
-7.500 -0.7361 0.03849 0.03055 -0.0350 1.0000 0.0276
-7.250 -0.7251 0.03585 0.02755 -0.0332 1.0000 0.0281
-7.000 -0.7115 0.03335 0.02469 -0.0315 1.0000 0.0289
-6.750 -0.6957 0.03102 0.02197 -0.0299 1.0000 0.0298
-6.500 -0.6783 0.02907 0.01976 -0.0284 1.0000 0.0310
-6.250 -0.6606 0.02784 0.01850 -0.0271 1.0000 0.0322
-6.000 -0.6422 0.02667 0.01724 -0.0258 1.0000 0.0339
-5.750 -0.6230 0.02551 0.01582 -0.0243 1.0000 0.0373
-5.500 -0.6051 0.02467 0.01508 -0.0232 1.0000 0.0402
-5.250 -0.5858 0.02392 0.01417 -0.0218 1.0000 0.0448
-5.000 -0.5675 0.02299 0.01332 -0.0206 1.0000 0.0485
-4.750 -0.5482 0.02227 0.01254 -0.0192 1.0000 0.0535
-4.500 -0.5297 0.02138 0.01165 -0.0178 1.0000 0.0572
-4.250 -0.5106 0.02077 0.01106 -0.0166 1.0000 0.0626
-4.000 -0.4917 0.02007 0.01034 -0.0153 1.0000 0.0675
-3.750 -0.4723 0.01950 0.00981 -0.0141 1.0000 0.0739
-3.500 -0.4525 0.01893 0.00921 -0.0131 1.0000 0.0811
-3.250 -0.4320 0.01842 0.00868 -0.0121 1.0000 0.0905
-3.000 -0.4095 0.01784 0.00813 -0.0118 0.9995 0.1042
-2.750 -0.3770 0.01718 0.00762 -0.0135 0.9956 0.1323
-2.500 -0.3468 0.01581 0.00685 -0.0154 0.9922 0.2473
-2.250 -0.3211 0.01505 0.00731 -0.0156 0.9879 0.5428
-2.000 -0.2883 0.01531 0.00755 -0.0165 0.9839 0.5870
-1.750 -0.2595 0.01553 0.00778 -0.0164 0.9785 0.6150
-1.500 -0.2287 0.01581 0.00806 -0.0167 0.9740 0.6394
-1.250 -0.1998 0.01604 0.00830 -0.0166 0.9691 0.6589
-1.000 -0.1704 0.01620 0.00845 -0.0168 0.9638 0.6740
-0.750 -0.1363 0.01628 0.00848 -0.0181 0.9598 0.6852
-0.500 -0.1073 0.01627 0.00846 -0.0183 0.9534 0.6907
-0.250 -0.0735 0.01624 0.00838 -0.0197 0.9483 0.6958
0.000 -0.0376 0.01622 0.00830 -0.0216 0.9442 0.7007
0.250 -0.0103 0.01620 0.00830 -0.0217 0.9375 0.7044
0.500 0.0243 0.01617 0.00829 -0.0231 0.9326 0.7086
0.750 0.0583 0.01610 0.00823 -0.0244 0.9252 0.7137
1.000 0.1004 0.01591 0.00807 -0.0270 0.9165 0.7185
1.250 0.1375 0.01569 0.00792 -0.0284 0.9046 0.7233
1.500 0.1774 0.01550 0.00778 -0.0304 0.8960 0.7292
1.750 0.2118 0.01538 0.00775 -0.0315 0.8873 0.7344
2.000 0.2478 0.01512 0.00760 -0.0324 0.8735 0.7395
2.250 0.2914 0.01465 0.00719 -0.0343 0.8524 0.7458
2.500 0.3252 0.01430 0.00692 -0.0344 0.8236 0.7515
2.750 0.3589 0.01400 0.00664 -0.0343 0.7813 0.7581
3.000 0.3893 0.01383 0.00629 -0.0334 0.6976 0.7650
3.250 0.4133 0.01445 0.00591 -0.0313 0.4775 0.7713
3.500 0.4280 0.01563 0.00622 -0.0290 0.3132 0.7794
3.750 0.4441 0.01681 0.00662 -0.0272 0.1603 0.7867
4.000 0.4651 0.01762 0.00710 -0.0261 0.1145 0.7960
4.250 0.4868 0.01821 0.00762 -0.0249 0.0982 0.8052
4.500 0.5091 0.01871 0.00819 -0.0237 0.0887 0.8155
4.750 0.5304 0.01935 0.00881 -0.0225 0.0819 0.8271
5.000 0.5521 0.01981 0.00938 -0.0212 0.0759 0.8391
5.250 0.5730 0.02037 0.00996 -0.0199 0.0712 0.8529
5.500 0.5937 0.02106 0.01071 -0.0185 0.0682 0.8698
5.750 0.6162 0.02169 0.01146 -0.0173 0.0657 0.8899
6.000 0.6416 0.02243 0.01230 -0.0168 0.0634 0.9176
6.500 0.7033 0.02442 0.01424 -0.0188 0.0581 1.0000
6.750 0.7303 0.02549 0.01540 -0.0188 0.0561 1.0000
7.000 0.7572 0.02670 0.01675 -0.0188 0.0546 1.0000
7.250 0.7835 0.02806 0.01824 -0.0187 0.0533 1.0000
7.500 0.8088 0.02951 0.01984 -0.0185 0.0522 1.0000
7.750 0.8329 0.03099 0.02147 -0.0181 0.0510 1.0000
8.000 0.8557 0.03236 0.02297 -0.0177 0.0497 1.0000
8.250 0.8776 0.03380 0.02445 -0.0172 0.0483 1.0000
8.500 0.8972 0.03576 0.02665 -0.0164 0.0472 1.0000
8.750 0.9143 0.03800 0.02929 -0.0151 0.0464 1.0000
9.000 0.9287 0.04054 0.03225 -0.0136 0.0458 1.0000
9.250 0.9399 0.04334 0.03546 -0.0118 0.0453 1.0000
9.500 0.9475 0.04642 0.03894 -0.0099 0.0449 1.0000
9.750 0.9513 0.04966 0.04257 -0.0079 0.0444 1.0000
10.000 0.9513 0.05298 0.04624 -0.0057 0.0437 1.0000
10.250 0.9481 0.05624 0.04980 -0.0036 0.0430 1.0000
10.500 0.9409 0.05956 0.05338 -0.0015 0.0425 1.0000
10.750 0.9269 0.06286 0.05688 0.0011 0.0421 1.0000
11.000 0.9056 0.06679 0.06101 0.0030 0.0420 1.0000
11.250 0.8755 0.07219 0.06662 0.0029 0.0422 1.0000
11.500 0.8365 0.08026 0.07488 -0.0010 0.0426 1.0000
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