NLR-7301 AIRFOIL (nlr7301-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NLR-7301 AIRFOIL (nlr7301-il) Reynolds number: 100,000 Max Cl/Cd: 21.5 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlr7301-il-100000.txt Download as CSV file: xf-nlr7301-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7978 0.06937 0.06245 -0.0695 1.0000 0.1013
-11.750 -0.8143 0.06582 0.05882 -0.0683 1.0000 0.1010
-11.500 -0.8382 0.06327 0.05621 -0.0651 1.0000 0.1007
-11.250 -0.8672 0.06151 0.05441 -0.0600 1.0000 0.1004
-11.000 -0.8932 0.05949 0.05229 -0.0553 1.0000 0.1002
-10.750 -0.9158 0.05731 0.04995 -0.0509 1.0000 0.0999
-10.500 -0.9339 0.05494 0.04738 -0.0469 1.0000 0.0998
-10.250 -0.9468 0.05245 0.04462 -0.0435 1.0000 0.0998
-10.000 -0.9538 0.04997 0.04186 -0.0405 1.0000 0.1001
-9.750 -0.9579 0.04758 0.03911 -0.0378 1.0000 0.1008
-9.500 -0.9553 0.04528 0.03650 -0.0357 1.0000 0.1018
-9.250 -0.9385 0.04380 0.03516 -0.0345 1.0000 0.1035
-9.000 -0.9257 0.04234 0.03364 -0.0331 1.0000 0.1052
-8.750 -0.9136 0.04067 0.03178 -0.0316 1.0000 0.1069
-8.500 -0.9004 0.03894 0.02978 -0.0303 1.0000 0.1086
-8.250 -0.8860 0.03734 0.02782 -0.0291 1.0000 0.1105
-8.000 -0.8674 0.03587 0.02638 -0.0282 1.0000 0.1130
-7.750 -0.8482 0.03486 0.02539 -0.0272 1.0000 0.1159
-7.500 -0.8290 0.03376 0.02413 -0.0263 1.0000 0.1191
-7.250 -0.8091 0.03257 0.02275 -0.0255 1.0000 0.1222
-7.000 -0.7887 0.03157 0.02190 -0.0246 1.0000 0.1258
-6.750 -0.7681 0.03075 0.02102 -0.0237 1.0000 0.1304
-6.500 -0.7473 0.02978 0.02005 -0.0228 1.0000 0.1350
-6.250 -0.7266 0.02901 0.01939 -0.0219 1.0000 0.1402
-6.000 -0.7052 0.02826 0.01857 -0.0212 1.0000 0.1466
-5.750 -0.6847 0.02749 0.01801 -0.0202 1.0000 0.1535
-5.500 -0.6633 0.02678 0.01734 -0.0195 1.0000 0.1619
-5.250 -0.6417 0.02614 0.01682 -0.0189 1.0000 0.1722
-5.000 -0.6202 0.02541 0.01631 -0.0183 1.0000 0.1844
-4.750 -0.5976 0.02472 0.01583 -0.0180 1.0000 0.2010
-4.500 -0.5736 0.02397 0.01533 -0.0181 1.0000 0.2264
-4.250 -0.5448 0.02257 0.01462 -0.0200 1.0000 0.2879
-4.000 -0.5219 0.02203 0.01583 -0.0192 1.0000 0.5276
-3.750 -0.5027 0.02315 0.01693 -0.0168 1.0000 0.5842
-3.500 -0.4886 0.02443 0.01822 -0.0129 1.0000 0.6077
-3.250 -0.4729 0.02557 0.01933 -0.0096 1.0000 0.6267
-3.000 -0.4591 0.02673 0.02049 -0.0058 1.0000 0.6414
-2.750 -0.4473 0.02784 0.02162 -0.0014 1.0000 0.6524
-2.500 -0.4251 0.02869 0.02241 -0.0001 0.9990 0.6685
-2.250 -0.4038 0.03026 0.02402 0.0035 0.9941 0.6774
-2.000 -0.3719 0.03119 0.02488 0.0030 0.9886 0.6924
-1.750 -0.3497 0.03239 0.02611 0.0059 0.9827 0.7018
-1.500 -0.3178 0.03314 0.02681 0.0052 0.9767 0.7156
-1.250 -0.2970 0.03400 0.02769 0.0080 0.9698 0.7265
-1.000 -0.2736 0.03501 0.02871 0.0105 0.9630 0.7425
-0.750 -0.2546 0.03566 0.02939 0.0135 0.9549 0.7605
-0.500 -0.2247 0.03642 0.03013 0.0138 0.9473 0.7779
-0.250 -0.2062 0.03643 0.03017 0.0164 0.9381 0.7859
0.000 -0.1633 0.03672 0.03042 0.0126 0.9296 0.7942
0.250 -0.1377 0.03651 0.03021 0.0126 0.9188 0.7997
0.500 -0.1010 0.03661 0.03032 0.0109 0.9087 0.8048
0.750 -0.0624 0.03652 0.03023 0.0083 0.8962 0.8102
1.000 0.0273 0.03587 0.02954 -0.0006 0.8702 0.8142
1.250 0.0735 0.03440 0.02808 -0.0014 0.8426 0.8175
1.500 0.1335 0.03318 0.02690 -0.0046 0.8278 0.8206
1.750 0.1632 0.03239 0.02615 -0.0044 0.8115 0.8239
2.000 0.2278 0.03090 0.02473 -0.0086 0.7992 0.8273
2.250 0.2865 0.02905 0.02294 -0.0116 0.7838 0.8304
2.500 0.3284 0.02733 0.02128 -0.0123 0.7629 0.8328
2.750 0.3578 0.02557 0.01959 -0.0100 0.7337 0.8355
3.000 0.3752 0.02411 0.01815 -0.0060 0.6781 0.8390
3.250 0.3920 0.02425 0.01617 -0.0010 0.3261 0.8417
3.500 0.3988 0.02532 0.01649 0.0015 0.2469 0.8446
3.750 0.4189 0.02595 0.01680 0.0019 0.2144 0.8474
4.000 0.4421 0.02653 0.01712 0.0019 0.1945 0.8507
4.250 0.4635 0.02689 0.01735 0.0029 0.1801 0.8540
4.500 0.4896 0.02744 0.01776 0.0030 0.1682 0.8571
4.750 0.5195 0.02817 0.01829 0.0021 0.1583 0.8600
5.000 0.5506 0.02880 0.01885 0.0011 0.1501 0.8630
5.250 0.5858 0.02978 0.01970 -0.0008 0.1433 0.8660
5.500 0.6118 0.03028 0.02021 -0.0006 0.1375 0.8693
5.750 0.6426 0.03127 0.02102 -0.0013 0.1328 0.8731
6.000 0.6709 0.03203 0.02194 -0.0015 0.1290 0.8770
6.250 0.7027 0.03304 0.02297 -0.0027 0.1258 0.8804
6.500 0.7334 0.03411 0.02401 -0.0037 0.1233 0.8836
6.750 0.7610 0.03550 0.02540 -0.0039 0.1213 0.8870
7.000 0.7836 0.03657 0.02677 -0.0033 0.1196 0.8911
7.250 0.8075 0.03787 0.02831 -0.0032 0.1176 0.8958
7.500 0.8288 0.03911 0.02974 -0.0026 0.1159 0.9003
7.750 0.8490 0.04045 0.03124 -0.0018 0.1146 0.9051
8.000 0.8706 0.04218 0.03316 -0.0015 0.1139 0.9097
8.250 0.8900 0.04413 0.03535 -0.0011 0.1136 0.9141
8.500 0.9028 0.04627 0.03782 0.0004 0.1137 0.9190
8.750 0.9109 0.04914 0.04111 0.0019 0.1145 0.9242
9.000 0.9127 0.05248 0.04491 0.0040 0.1159 0.9296
9.250 0.9097 0.05589 0.04870 0.0063 0.1175 0.9361
9.500 0.9079 0.05934 0.05244 0.0079 0.1188 0.9428
9.750 0.9067 0.06266 0.05598 0.0095 0.1199 0.9504
10.000 0.9124 0.06614 0.05958 0.0100 0.1209 0.9582
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Polar data table (+)
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