NLR-7301 AIRFOIL (nlr7301-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-7301 AIRFOIL (nlr7301-il) Reynolds number: 50,000 Max Cl/Cd: 18.66 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlr7301-il-50000-n5.txt Download as CSV file: xf-nlr7301-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NLR-7301 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5453 0.10946 0.10043 -0.0470 1.0000 0.0914
-12.500 -0.6182 0.09099 0.08177 -0.0584 1.0000 0.0911
-12.250 -0.6814 0.07901 0.06954 -0.0650 1.0000 0.0905
-12.000 -0.7227 0.07189 0.06217 -0.0676 1.0000 0.0905
-11.750 -0.7539 0.06682 0.05688 -0.0683 1.0000 0.0908
-11.500 -0.7798 0.06297 0.05281 -0.0674 1.0000 0.0912
-11.250 -0.8039 0.06004 0.04968 -0.0651 1.0000 0.0917
-11.000 -0.8285 0.05788 0.04736 -0.0613 1.0000 0.0922
-10.750 -0.8500 0.05586 0.04513 -0.0574 1.0000 0.0927
-10.500 -0.8468 0.05447 0.04378 -0.0549 1.0000 0.0938
-10.250 -0.8472 0.05311 0.04240 -0.0521 1.0000 0.0950
-10.000 -0.8486 0.05171 0.04092 -0.0493 1.0000 0.0964
-9.750 -0.8503 0.05021 0.03928 -0.0464 1.0000 0.0981
-9.500 -0.8516 0.04858 0.03741 -0.0436 1.0000 0.1000
-9.250 -0.8479 0.04703 0.03568 -0.0411 1.0000 0.1019
-9.000 -0.8357 0.04593 0.03464 -0.0392 1.0000 0.1039
-8.750 -0.8253 0.04477 0.03342 -0.0372 1.0000 0.1064
-8.500 -0.8155 0.04352 0.03200 -0.0352 1.0000 0.1093
-8.250 -0.8024 0.04240 0.03081 -0.0334 1.0000 0.1123
-8.000 -0.7874 0.04152 0.02999 -0.0316 1.0000 0.1154
-7.750 -0.7725 0.04058 0.02896 -0.0298 1.0000 0.1193
-7.500 -0.7563 0.03974 0.02811 -0.0281 1.0000 0.1233
-7.250 -0.7404 0.03902 0.02744 -0.0263 1.0000 0.1277
-7.000 -0.7238 0.03832 0.02659 -0.0245 1.0000 0.1331
-6.750 -0.7080 0.03767 0.02612 -0.0226 1.0000 0.1381
-6.500 -0.6928 0.03702 0.02541 -0.0207 1.0000 0.1446
-6.250 -0.6788 0.03634 0.02485 -0.0188 1.0000 0.1508
-6.000 -0.6647 0.03567 0.02415 -0.0170 1.0000 0.1592
-5.750 -0.6449 0.03487 0.02353 -0.0164 0.9979 0.1687
-5.500 -0.6218 0.03405 0.02282 -0.0166 0.9946 0.1816
-5.250 -0.5994 0.03315 0.02208 -0.0170 0.9917 0.1980
-5.000 -0.5779 0.03210 0.02125 -0.0174 0.9880 0.2203
-4.750 -0.5551 0.03085 0.02037 -0.0185 0.9842 0.2558
-4.500 -0.5315 0.02949 0.01971 -0.0198 0.9809 0.3262
-4.250 -0.5143 0.03009 0.02135 -0.0159 0.9777 0.4280
-4.000 -0.4921 0.03126 0.02272 -0.0131 0.9737 0.5041
-3.750 -0.4634 0.03187 0.02318 -0.0133 0.9695 0.5510
-3.500 -0.4327 0.03254 0.02371 -0.0139 0.9659 0.5836
-3.250 -0.4103 0.03334 0.02442 -0.0122 0.9617 0.6048
-3.000 -0.3861 0.03407 0.02506 -0.0111 0.9571 0.6245
-2.750 -0.3613 0.03518 0.02614 -0.0088 0.9529 0.6396
-2.500 -0.3343 0.03630 0.02722 -0.0071 0.9494 0.6568
-2.250 -0.3178 0.03707 0.02798 -0.0039 0.9440 0.6745
-2.000 -0.2963 0.03782 0.02871 -0.0017 0.9389 0.6934
-1.750 -0.2704 0.03847 0.02931 -0.0004 0.9345 0.7100
-1.500 -0.2450 0.03878 0.02959 0.0008 0.9301 0.7192
-1.250 -0.2251 0.03871 0.02949 0.0017 0.9238 0.7281
-1.000 -0.1971 0.03857 0.02930 0.0006 0.9182 0.7365
-0.750 -0.1648 0.03867 0.02937 -0.0001 0.9136 0.7419
-0.500 -0.1447 0.03854 0.02922 0.0006 0.9066 0.7484
-0.250 -0.1162 0.03837 0.02901 -0.0010 0.8995 0.7552
0.000 -0.0828 0.03837 0.02902 -0.0022 0.8938 0.7594
0.250 -0.0604 0.03830 0.02896 -0.0017 0.8858 0.7638
0.500 -0.0326 0.03823 0.02890 -0.0024 0.8774 0.7687
0.750 0.0078 0.03820 0.02888 -0.0054 0.8710 0.7735
1.000 0.0289 0.03807 0.02878 -0.0053 0.8597 0.7778
1.250 0.0654 0.03796 0.02873 -0.0066 0.8508 0.7810
1.500 0.0915 0.03774 0.02858 -0.0064 0.8368 0.7849
1.750 0.1367 0.03683 0.02771 -0.0079 0.8137 0.7882
2.000 0.2043 0.03474 0.02565 -0.0109 0.7818 0.7906
2.250 0.2298 0.03372 0.02467 -0.0097 0.7537 0.7949
2.500 0.2543 0.03284 0.02388 -0.0080 0.7290 0.7985
2.750 0.2766 0.03196 0.02309 -0.0058 0.7014 0.8019
3.000 0.2916 0.03141 0.02264 -0.0033 0.6654 0.8057
3.250 0.3136 0.03064 0.02193 -0.0016 0.6135 0.8095
3.500 0.3797 0.02875 0.01884 -0.0023 0.4124 0.8119
3.750 0.3873 0.02981 0.01904 0.0004 0.3055 0.8161
4.000 0.3959 0.03071 0.01947 0.0029 0.2537 0.8199
4.250 0.4109 0.03150 0.01996 0.0042 0.2224 0.8237
4.500 0.4307 0.03222 0.02047 0.0048 0.2010 0.8274
4.750 0.4542 0.03294 0.02100 0.0047 0.1845 0.8313
5.000 0.4775 0.03355 0.02149 0.0051 0.1721 0.8350
5.250 0.5015 0.03413 0.02195 0.0055 0.1616 0.8389
5.500 0.5305 0.03471 0.02252 0.0052 0.1519 0.8431
5.750 0.5635 0.03542 0.02312 0.0041 0.1438 0.8472
6.000 0.5983 0.03613 0.02381 0.0028 0.1364 0.8508
6.250 0.6303 0.03685 0.02448 0.0022 0.1307 0.8542
6.500 0.6617 0.03764 0.02531 0.0016 0.1254 0.8582
6.750 0.6936 0.03856 0.02608 0.0007 0.1213 0.8627
7.000 0.7234 0.03962 0.02734 0.0001 0.1170 0.8674
7.250 0.7502 0.04061 0.02839 0.0001 0.1141 0.8720
7.500 0.7786 0.04173 0.02945 -0.0003 0.1117 0.8770
7.750 0.8049 0.04318 0.03109 -0.0007 0.1092 0.8819
8.000 0.8257 0.04454 0.03269 -0.0001 0.1068 0.8866
8.250 0.8468 0.04586 0.03414 0.0002 0.1045 0.8919
8.500 0.8695 0.04721 0.03552 0.0002 0.1026 0.8977
8.750 0.8885 0.04866 0.03706 0.0008 0.1011 0.9037
9.000 0.9006 0.05075 0.03954 0.0020 0.0999 0.9106
9.250 0.9101 0.05291 0.04205 0.0034 0.0989 0.9175
9.500 0.9172 0.05525 0.04470 0.0047 0.0981 0.9252
9.750 0.9206 0.05768 0.04745 0.0062 0.0974 0.9334
10.000 0.9197 0.06021 0.05029 0.0078 0.0967 0.9432
10.250 0.9156 0.06299 0.05338 0.0092 0.0961 0.9564
10.500 0.9059 0.06605 0.05674 0.0102 0.0956 0.9987
10.750 0.8946 0.06997 0.06092 0.0102 0.0951 1.0000
11.000 0.8745 0.07477 0.06601 0.0096 0.0948 1.0000
11.250 0.8344 0.08202 0.07361 0.0074 0.0950 1.0000
11.500 0.7304 0.10090 0.09305 -0.0040 0.0968 1.0000
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Polar data table (+)
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