NLR-7223-62 AIRFOIL (nl722362-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-7223-62 AIRFOIL (nl722362-il) Reynolds number: 50,000 Max Cl/Cd: 30.01 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nl722362-il-50000.txt Download as CSV file: xf-nl722362-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NLR-7223-62 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4739 0.10236 0.09544 -0.0097 1.0000 0.2864
-8.500 -0.4727 0.09952 0.09268 -0.0089 1.0000 0.3025
-8.250 -0.4776 0.09717 0.09041 -0.0080 1.0000 0.3195
-8.000 -0.4635 0.09324 0.08652 -0.0061 1.0000 0.3406
-7.750 -0.4615 0.09074 0.08408 -0.0041 1.0000 0.3647
-7.500 -0.4487 0.08732 0.08070 -0.0018 1.0000 0.3913
-7.250 -0.4418 0.08458 0.07802 0.0008 1.0000 0.4204
-7.000 -0.4346 0.08212 0.07562 0.0041 1.0000 0.4577
-6.750 -0.4136 0.07890 0.07240 0.0072 1.0000 0.5007
-4.750 -0.5459 0.04714 0.03903 -0.0046 1.0000 0.1647
-4.500 -0.5285 0.04377 0.03470 -0.0022 1.0000 0.1362
-4.250 -0.5105 0.04027 0.03113 -0.0007 1.0000 0.1310
-4.000 -0.4919 0.03761 0.02776 0.0017 1.0000 0.1227
-3.750 -0.4712 0.03547 0.02515 0.0037 1.0000 0.1191
-3.500 -0.4490 0.03307 0.02246 0.0053 1.0000 0.1161
-3.250 -0.4247 0.03094 0.01995 0.0068 1.0000 0.1137
-3.000 -0.3989 0.02910 0.01776 0.0081 1.0000 0.1136
-2.750 -0.3725 0.02764 0.01602 0.0092 1.0000 0.1177
-2.500 -0.1426 0.01972 0.01157 -0.0218 1.0000 1.0000
-2.250 -0.1313 0.01961 0.01089 -0.0188 1.0000 1.0000
-2.000 -0.1198 0.01952 0.01040 -0.0161 1.0000 1.0000
-1.750 -0.1074 0.01947 0.01004 -0.0136 1.0000 1.0000
-1.500 -0.0941 0.01945 0.00974 -0.0113 1.0000 1.0000
-1.250 -0.0801 0.01945 0.00951 -0.0090 1.0000 1.0000
-1.000 -0.0655 0.01948 0.00930 -0.0069 1.0000 1.0000
-0.750 -0.0504 0.01953 0.00916 -0.0048 1.0000 1.0000
-0.500 -0.0349 0.01961 0.00907 -0.0029 1.0000 1.0000
-0.250 -0.0191 0.01971 0.00902 -0.0010 1.0000 1.0000
0.000 -0.0030 0.01983 0.00901 0.0009 1.0000 1.0000
0.250 0.0132 0.01997 0.00904 0.0026 1.0000 1.0000
0.500 0.0297 0.02014 0.00911 0.0043 1.0000 1.0000
0.750 0.0461 0.02033 0.00924 0.0060 1.0000 1.0000
1.000 0.0627 0.02056 0.00940 0.0076 1.0000 1.0000
1.250 0.0792 0.02081 0.00961 0.0091 1.0000 1.0000
1.500 0.0955 0.02109 0.00988 0.0106 1.0000 1.0000
1.750 0.1116 0.02142 0.01021 0.0121 1.0000 1.0000
2.000 0.1274 0.02179 0.01059 0.0135 1.0000 1.0000
2.250 0.1428 0.02222 0.01105 0.0148 1.0000 1.0000
2.500 0.1576 0.02271 0.01159 0.0161 1.0000 1.0000
2.750 0.1717 0.02329 0.01224 0.0173 1.0000 1.0000
3.000 0.1963 0.02414 0.01321 0.0161 0.9956 1.0000
3.250 0.3306 0.02546 0.01505 -0.0050 0.9408 1.0000
3.500 0.4707 0.02420 0.01455 -0.0229 0.8724 1.0000
3.750 0.5816 0.01938 0.00998 -0.0277 0.6514 1.0000
4.000 0.6168 0.02071 0.00990 -0.0263 0.5033 1.0000
4.250 0.6431 0.02196 0.01078 -0.0256 0.4531 1.0000
4.500 0.6715 0.02309 0.01177 -0.0255 0.4213 1.0000
4.750 0.6995 0.02421 0.01278 -0.0252 0.3973 1.0000
5.000 0.7245 0.02531 0.01398 -0.0246 0.3770 1.0000
5.250 0.7484 0.02647 0.01521 -0.0237 0.3590 1.0000
5.500 0.7714 0.02773 0.01659 -0.0228 0.3425 1.0000
5.750 0.7934 0.02906 0.01805 -0.0217 0.3266 1.0000
6.000 0.8144 0.03049 0.01963 -0.0204 0.3108 1.0000
6.250 0.8342 0.03206 0.02138 -0.0190 0.2951 1.0000
6.500 0.8529 0.03369 0.02319 -0.0173 0.2783 1.0000
6.750 0.8707 0.03547 0.02512 -0.0156 0.2615 1.0000
7.000 0.8885 0.03737 0.02707 -0.0138 0.2436 1.0000
7.250 0.8996 0.03942 0.02943 -0.0112 0.2251 1.0000
7.500 0.9094 0.04145 0.03175 -0.0084 0.2055 1.0000
7.750 0.9242 0.04311 0.03339 -0.0062 0.1844 1.0000
8.000 0.9362 0.04540 0.03572 -0.0038 0.1669 1.0000
8.500 0.9351 0.05183 0.04306 0.0033 0.1469 1.0000
8.750 0.9485 0.05442 0.04560 0.0051 0.1372 1.0000
9.000 0.9340 0.05889 0.05061 0.0091 0.1356 1.0000
9.250 0.9176 0.06345 0.05553 0.0124 0.1345 1.0000
9.500 0.8988 0.06808 0.06041 0.0152 0.1343 1.0000
9.750 0.8773 0.07282 0.06530 0.0175 0.1348 1.0000
10.000 0.8559 0.07747 0.07001 0.0194 0.1359 1.0000
10.250 0.8369 0.08224 0.07480 0.0205 0.1369 1.0000
10.500 0.8213 0.08755 0.08011 0.0203 0.1377 1.0000
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Polar data table (+)
Polar graphs
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