NLR-7223-62 AIRFOIL (nl722362-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-7223-62 AIRFOIL (nl722362-il) Reynolds number: 100,000 Max Cl/Cd: 42.22 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nl722362-il-100000.txt Download as CSV file: xf-nl722362-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4888 0.10225 0.09719 -0.0249 1.0000 0.0886
-9.250 -0.5072 0.09897 0.09402 -0.0308 1.0000 0.0903
-9.000 -0.5248 0.09539 0.09053 -0.0356 1.0000 0.0907
-8.750 -0.4972 0.09070 0.08583 -0.0293 1.0000 0.0946
-8.500 -0.4944 0.08764 0.08282 -0.0291 1.0000 0.0977
-8.250 -0.5038 0.08419 0.07944 -0.0307 1.0000 0.1003
-8.000 -0.5228 0.08132 0.07664 -0.0307 1.0000 0.1022
-7.750 -0.5497 0.07898 0.07430 -0.0303 1.0000 0.1043
-7.500 -0.5830 0.07820 0.07336 -0.0275 1.0000 0.1054
-7.250 -0.5819 0.07329 0.06856 -0.0255 1.0000 0.1074
-7.000 -0.5704 0.07032 0.06570 -0.0226 1.0000 0.1113
-6.750 -0.5769 0.06798 0.06332 -0.0199 1.0000 0.1156
-6.500 -0.6055 0.06710 0.06196 -0.0169 1.0000 0.1214
-6.250 -0.5890 0.06225 0.05743 -0.0151 1.0000 0.1254
-6.000 -0.6027 0.06162 0.05630 -0.0120 1.0000 0.1365
-5.750 -0.5884 0.05689 0.05189 -0.0103 1.0000 0.1406
-5.500 -0.5890 0.05455 0.04933 -0.0078 1.0000 0.1534
-3.750 -0.4883 0.03304 0.02486 0.0086 1.0000 0.0921
-3.500 -0.4629 0.02981 0.02126 0.0105 1.0000 0.0744
-3.250 -0.4392 0.02710 0.01811 0.0123 1.0000 0.0674
-3.000 -0.4147 0.02631 0.01674 0.0145 1.0000 0.0633
-2.750 -0.3901 0.02440 0.01465 0.0155 1.0000 0.0625
-2.500 -0.3656 0.02261 0.01277 0.0165 1.0000 0.0653
-2.250 -0.3419 0.02146 0.01158 0.0175 1.0000 0.0679
-2.000 -0.3184 0.02042 0.01053 0.0188 1.0000 0.0707
-1.750 -0.1195 0.01555 0.00913 -0.0119 1.0000 1.0000
-1.500 -0.1062 0.01553 0.00886 -0.0094 1.0000 1.0000
-1.250 -0.0922 0.01555 0.00868 -0.0072 1.0000 1.0000
-1.000 -0.0774 0.01559 0.00853 -0.0050 1.0000 1.0000
-0.750 -0.0620 0.01565 0.00844 -0.0029 1.0000 1.0000
-0.500 -0.0463 0.01574 0.00840 -0.0010 1.0000 1.0000
-0.250 -0.0302 0.01585 0.00839 0.0009 1.0000 1.0000
0.000 -0.0138 0.01598 0.00843 0.0027 1.0000 1.0000
0.250 0.0026 0.01614 0.00849 0.0045 1.0000 1.0000
0.500 0.0192 0.01632 0.00861 0.0062 1.0000 1.0000
0.750 0.0358 0.01653 0.00876 0.0078 1.0000 1.0000
1.000 0.0524 0.01677 0.00896 0.0094 1.0000 1.0000
1.250 0.1042 0.01726 0.00944 0.0037 0.9902 1.0000
1.500 0.1835 0.01775 0.00995 -0.0070 0.9721 1.0000
1.750 0.2458 0.01787 0.01014 -0.0140 0.9554 1.0000
2.000 0.3111 0.01776 0.01013 -0.0212 0.9376 1.0000
2.250 0.3843 0.01734 0.00988 -0.0294 0.9191 1.0000
2.500 0.4735 0.01630 0.00907 -0.0400 0.8984 1.0000
2.750 0.5218 0.01530 0.00827 -0.0419 0.8665 1.0000
3.000 0.5474 0.01442 0.00749 -0.0392 0.8164 1.0000
3.250 0.5763 0.01365 0.00562 -0.0351 0.5429 1.0000
3.500 0.5876 0.01507 0.00601 -0.0315 0.4029 1.0000
3.750 0.6067 0.01597 0.00649 -0.0298 0.3554 1.0000
4.000 0.6281 0.01671 0.00701 -0.0286 0.3291 1.0000
4.250 0.6506 0.01738 0.00755 -0.0276 0.3103 1.0000
4.500 0.6735 0.01804 0.00815 -0.0266 0.2950 1.0000
4.750 0.6967 0.01870 0.00878 -0.0258 0.2821 1.0000
5.000 0.7201 0.01941 0.00944 -0.0250 0.2704 1.0000
5.250 0.7436 0.02012 0.01011 -0.0242 0.2593 1.0000
5.500 0.7662 0.02078 0.01091 -0.0232 0.2480 1.0000
5.750 0.7891 0.02157 0.01176 -0.0223 0.2373 1.0000
6.000 0.8117 0.02240 0.01257 -0.0215 0.2259 1.0000
6.250 0.8334 0.02319 0.01343 -0.0204 0.2138 1.0000
6.500 0.8537 0.02397 0.01437 -0.0190 0.2007 1.0000
6.750 0.8724 0.02464 0.01510 -0.0175 0.1855 1.0000
7.000 0.8898 0.02516 0.01561 -0.0159 0.1690 1.0000
7.250 0.9066 0.02579 0.01624 -0.0141 0.1522 1.0000
7.500 0.9201 0.02628 0.01698 -0.0116 0.1336 1.0000
7.750 0.9331 0.02669 0.01744 -0.0090 0.1142 1.0000
8.000 0.9461 0.02732 0.01810 -0.0064 0.0969 1.0000
8.250 0.9614 0.02846 0.01934 -0.0041 0.0844 1.0000
8.500 0.9770 0.02981 0.02068 -0.0021 0.0757 1.0000
8.750 0.9931 0.03145 0.02250 -0.0002 0.0693 1.0000
9.000 1.0098 0.03397 0.02513 0.0014 0.0656 1.0000
9.250 1.0210 0.03636 0.02800 0.0041 0.0625 1.0000
9.500 1.0319 0.03831 0.03018 0.0065 0.0592 1.0000
9.750 1.0442 0.04068 0.03260 0.0082 0.0567 1.0000
10.000 1.0470 0.04424 0.03652 0.0112 0.0558 1.0000
10.250 1.0438 0.04746 0.04019 0.0149 0.0555 1.0000
10.500 1.0358 0.05087 0.04400 0.0188 0.0554 1.0000
10.750 1.0226 0.05439 0.04789 0.0229 0.0554 1.0000
11.000 1.0065 0.05792 0.05168 0.0268 0.0555 1.0000
11.250 0.9865 0.06123 0.05518 0.0309 0.0557 1.0000
11.500 0.9656 0.06495 0.05907 0.0338 0.0559 1.0000
11.750 0.9422 0.06893 0.06325 0.0355 0.0562 1.0000
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Polar data table (+)
Polar graphs
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