NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-7223-43 AIRFOIL (nl722343-il) Reynolds number: 100,000 Max Cl/Cd: 42.52 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nl722343-il-100000.txt Download as CSV file: xf-nl722343-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NLR-7223-43 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4937 0.09714 0.09204 -0.0239 1.0000 0.0948
-8.750 -0.5107 0.09350 0.08851 -0.0288 1.0000 0.0973
-8.500 -0.5350 0.08975 0.08488 -0.0333 1.0000 0.0979
-8.250 -0.5119 0.08563 0.08077 -0.0288 1.0000 0.1023
-8.000 -0.5117 0.08267 0.07786 -0.0282 1.0000 0.1060
-7.750 -0.5251 0.07901 0.07427 -0.0302 1.0000 0.1083
-7.500 -0.5486 0.07551 0.07070 -0.0339 1.0000 0.1120
-7.000 -0.5442 0.06822 0.06349 -0.0316 1.0000 0.1194
-6.750 -0.5618 0.06685 0.06172 -0.0330 1.0000 0.1281
-6.500 -0.5503 0.06165 0.05678 -0.0309 1.0000 0.1321
-6.250 -0.5560 0.05999 0.05473 -0.0308 1.0000 0.1442
-6.000 -0.5420 0.05589 0.05094 -0.0282 1.0000 0.1495
-5.750 -0.5381 0.05306 0.04799 -0.0273 1.0000 0.1626
-5.500 -0.5310 0.05039 0.04526 -0.0259 1.0000 0.1779
-5.250 -0.5220 0.04784 0.04270 -0.0241 1.0000 0.1954
-5.000 -0.5144 0.04552 0.04032 -0.0226 1.0000 0.2231
-4.250 -0.4224 0.03157 0.02369 -0.0227 1.0000 0.0812
-4.000 -0.3985 0.02853 0.02024 -0.0216 1.0000 0.0742
-3.750 -0.3728 0.02703 0.01819 -0.0199 1.0000 0.0687
-3.500 -0.3484 0.02472 0.01567 -0.0190 1.0000 0.0662
-3.250 -0.3233 0.02299 0.01370 -0.0179 1.0000 0.0647
-3.000 -0.2981 0.02158 0.01213 -0.0168 1.0000 0.0646
-2.750 -0.2737 0.02044 0.01089 -0.0157 1.0000 0.0662
-2.500 -0.2500 0.01947 0.00986 -0.0146 1.0000 0.0710
-2.250 -0.2277 0.01834 0.00888 -0.0135 1.0000 0.0769
-2.000 -0.2052 0.01754 0.00807 -0.0122 1.0000 0.0850
-1.750 -0.1827 0.01663 0.00727 -0.0112 1.0000 0.1126
-1.500 -0.1882 0.01457 0.00809 -0.0026 1.0000 0.7792
-1.250 -0.0366 0.01569 0.00907 -0.0149 1.0000 1.0000
-1.000 -0.0320 0.01555 0.00887 -0.0117 1.0000 1.0000
-0.750 -0.0280 0.01541 0.00866 -0.0084 1.0000 1.0000
-0.500 -0.0248 0.01525 0.00846 -0.0051 1.0000 1.0000
-0.250 -0.0223 0.01507 0.00824 -0.0017 1.0000 1.0000
0.000 -0.0198 0.01487 0.00801 0.0017 1.0000 1.0000
0.250 -0.0146 0.01470 0.00781 0.0046 1.0000 1.0000
0.500 -0.0017 0.01467 0.00773 0.0061 1.0000 1.0000
0.750 0.0166 0.01476 0.00776 0.0066 1.0000 1.0000
1.000 0.0374 0.01493 0.00789 0.0067 1.0000 1.0000
1.250 0.1096 0.01568 0.00862 -0.0025 0.9818 1.0000
1.500 0.1734 0.01603 0.00897 -0.0098 0.9642 1.0000
1.750 0.2331 0.01614 0.00913 -0.0160 0.9484 1.0000
2.000 0.2963 0.01603 0.00911 -0.0223 0.9322 1.0000
2.250 0.3553 0.01565 0.00885 -0.0275 0.9128 1.0000
2.500 0.4258 0.01497 0.00835 -0.0341 0.8920 1.0000
2.750 0.4840 0.01409 0.00764 -0.0380 0.8610 1.0000
3.000 0.5220 0.01328 0.00694 -0.0379 0.8057 1.0000
3.250 0.5651 0.01329 0.00572 -0.0373 0.5252 1.0000
3.500 0.5703 0.01445 0.00603 -0.0331 0.4093 1.0000
3.750 0.5827 0.01526 0.00644 -0.0306 0.3633 1.0000
4.000 0.6009 0.01599 0.00693 -0.0292 0.3361 1.0000
4.250 0.6237 0.01667 0.00747 -0.0286 0.3155 1.0000
4.500 0.6486 0.01736 0.00807 -0.0284 0.2994 1.0000
4.750 0.6746 0.01808 0.00871 -0.0283 0.2854 1.0000
5.000 0.7014 0.01886 0.00941 -0.0285 0.2732 1.0000
5.250 0.7279 0.01955 0.01015 -0.0285 0.2612 1.0000
5.500 0.7545 0.02032 0.01099 -0.0285 0.2497 1.0000
5.750 0.7810 0.02118 0.01189 -0.0285 0.2384 1.0000
6.000 0.8073 0.02209 0.01277 -0.0285 0.2266 1.0000
6.250 0.8328 0.02295 0.01367 -0.0283 0.2139 1.0000
6.500 0.8568 0.02376 0.01461 -0.0279 0.1999 1.0000
6.750 0.8798 0.02452 0.01538 -0.0274 0.1839 1.0000
7.000 0.9006 0.02510 0.01604 -0.0265 0.1660 1.0000
7.250 0.9202 0.02559 0.01671 -0.0253 0.1468 1.0000
7.500 0.9391 0.02600 0.01713 -0.0241 0.1268 1.0000
7.750 0.9569 0.02675 0.01801 -0.0225 0.1052 1.0000
8.000 0.9755 0.02728 0.01848 -0.0211 0.0894 1.0000
8.250 0.9961 0.02885 0.02013 -0.0199 0.0788 1.0000
8.500 1.0163 0.03095 0.02245 -0.0188 0.0714 1.0000
8.750 1.0365 0.03285 0.02425 -0.0181 0.0655 1.0000
9.000 1.0535 0.03573 0.02765 -0.0165 0.0627 1.0000
9.250 1.0672 0.03880 0.03121 -0.0148 0.0605 1.0000
9.500 1.0792 0.04166 0.03441 -0.0131 0.0584 1.0000
9.750 1.0915 0.04415 0.03707 -0.0117 0.0562 1.0000
10.000 1.0981 0.04833 0.04142 -0.0103 0.0545 1.0000
10.250 1.0941 0.05209 0.04569 -0.0075 0.0542 1.0000
10.500 1.0853 0.05637 0.05040 -0.0049 0.0542 1.0000
10.750 1.0726 0.06075 0.05510 -0.0025 0.0543 1.0000
11.000 1.0558 0.06499 0.05956 0.0000 0.0545 1.0000
11.250 1.0324 0.06870 0.06355 0.0022 0.0549 1.0000
11.500 0.9021 0.08956 0.08495 -0.0105 0.0630 1.0000
11.750 0.8814 0.09982 0.09518 -0.0169 0.0643 1.0000
12.000 0.8738 0.10671 0.10205 -0.0198 0.0650 1.0000
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Polar data table (+)
Polar graphs
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