NLR-7223-62 AIRFOIL (nl722362-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NLR-7223-62 AIRFOIL (nl722362-il) Reynolds number: 1,000,000 Max Cl/Cd: 78.85 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nl722362-il-1000000-n5.txt Download as CSV file: xf-nl722362-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5205 0.07147 0.06983 -0.0444 0.9673 0.0044
-8.250 -0.6657 0.02291 0.01893 -0.0399 0.8911 0.0051
-8.000 -0.6586 0.01930 0.01477 -0.0367 0.8879 0.0053
-7.750 -0.6392 0.01809 0.01335 -0.0355 0.8857 0.0054
-7.500 -0.6180 0.01712 0.01223 -0.0345 0.8839 0.0055
-7.250 -0.5956 0.01627 0.01125 -0.0336 0.8823 0.0056
-7.000 -0.5723 0.01557 0.01045 -0.0329 0.8806 0.0058
-6.750 -0.5487 0.01490 0.00966 -0.0322 0.8790 0.0059
-6.500 -0.5251 0.01418 0.00883 -0.0315 0.8774 0.0061
-6.250 -0.5003 0.01373 0.00830 -0.0310 0.8760 0.0064
-6.000 -0.4760 0.01309 0.00755 -0.0303 0.8746 0.0068
-5.750 -0.4519 0.01243 0.00678 -0.0296 0.8733 0.0069
-5.500 -0.4269 0.01199 0.00626 -0.0290 0.8721 0.0072
-5.250 -0.4019 0.01157 0.00577 -0.0285 0.8709 0.0073
-5.000 -0.3786 0.01090 0.00501 -0.0276 0.8697 0.0075
-4.750 -0.3540 0.01046 0.00454 -0.0270 0.8687 0.0078
-4.500 -0.3288 0.01011 0.00417 -0.0264 0.8676 0.0081
-4.250 -0.3034 0.00981 0.00385 -0.0260 0.8665 0.0083
-4.000 -0.2778 0.00951 0.00352 -0.0255 0.8651 0.0086
-3.750 -0.2521 0.00925 0.00325 -0.0250 0.8635 0.0089
-3.500 -0.2263 0.00901 0.00299 -0.0246 0.8618 0.0093
-3.250 -0.2006 0.00879 0.00274 -0.0241 0.8583 0.0097
-3.000 -0.1748 0.00854 0.00245 -0.0236 0.8562 0.0101
-2.750 -0.1489 0.00833 0.00223 -0.0231 0.8537 0.0107
-2.500 -0.1230 0.00814 0.00204 -0.0226 0.8481 0.0116
-2.250 -0.0978 0.00798 0.00183 -0.0219 0.8372 0.0123
-2.000 -0.0727 0.00782 0.00162 -0.0212 0.8226 0.0140
-1.750 -0.0473 0.00769 0.00146 -0.0205 0.8082 0.0174
-1.500 -0.0215 0.00752 0.00134 -0.0200 0.7978 0.0304
-1.250 0.0039 0.00730 0.00123 -0.0195 0.7894 0.0640
-1.000 0.0286 0.00703 0.00112 -0.0189 0.7757 0.1230
-0.750 0.0456 0.00689 0.00096 -0.0166 0.6823 0.2240
-0.500 0.0596 0.00653 0.00094 -0.0140 0.6107 0.4113
-0.250 0.0701 0.00593 0.00093 -0.0107 0.5537 0.6450
0.000 0.0797 0.00552 0.00095 -0.0067 0.5037 0.8075
0.250 0.1478 0.00601 0.00149 -0.0155 0.4157 0.9377
0.500 0.1648 0.00628 0.00159 -0.0130 0.3748 0.9498
0.750 0.1948 0.00659 0.00170 -0.0136 0.3273 0.9545
1.000 0.2134 0.00688 0.00182 -0.0115 0.2902 0.9630
1.250 0.2518 0.00720 0.00195 -0.0139 0.2487 0.9653
1.500 0.2845 0.00743 0.00204 -0.0151 0.2203 0.9675
1.750 0.3139 0.00762 0.00213 -0.0155 0.2002 0.9700
2.000 0.3377 0.00779 0.00223 -0.0147 0.1859 0.9735
2.250 0.3626 0.00793 0.00231 -0.0140 0.1760 0.9757
2.500 0.3947 0.00807 0.00238 -0.0151 0.1664 0.9764
2.750 0.4267 0.00818 0.00246 -0.0161 0.1602 0.9773
3.000 0.4573 0.00832 0.00255 -0.0168 0.1530 0.9782
3.250 0.4872 0.00843 0.00264 -0.0174 0.1478 0.9792
3.500 0.5162 0.00856 0.00273 -0.0178 0.1424 0.9803
3.750 0.5458 0.00870 0.00286 -0.0182 0.1378 0.9818
4.000 0.5743 0.00882 0.00298 -0.0185 0.1351 0.9837
4.250 0.5999 0.00897 0.00313 -0.0180 0.1316 0.9861
4.500 0.6334 0.00910 0.00324 -0.0195 0.1280 0.9868
4.750 0.6664 0.00924 0.00337 -0.0208 0.1230 0.9877
5.000 0.6987 0.00937 0.00348 -0.0219 0.1159 0.9887
5.250 0.7295 0.00953 0.00361 -0.0228 0.1093 0.9897
5.500 0.7593 0.00970 0.00375 -0.0234 0.0987 0.9908
5.750 0.7881 0.01002 0.00395 -0.0239 0.0776 0.9922
6.000 0.8161 0.01035 0.00421 -0.0242 0.0627 0.9937
6.250 0.8418 0.01073 0.00451 -0.0241 0.0489 0.9949
6.500 0.8685 0.01108 0.00480 -0.0242 0.0372 0.9954
6.750 0.8946 0.01150 0.00514 -0.0242 0.0253 0.9959
7.000 0.9205 0.01186 0.00549 -0.0241 0.0196 0.9965
7.250 0.9458 0.01218 0.00581 -0.0238 0.0169 0.9970
7.500 0.9708 0.01251 0.00615 -0.0235 0.0147 0.9974
7.750 0.9957 0.01283 0.00650 -0.0232 0.0135 0.9979
8.000 1.0202 0.01321 0.00690 -0.0228 0.0124 0.9984
8.250 1.0446 0.01357 0.00730 -0.0224 0.0116 0.9988
8.500 1.0697 0.01393 0.00770 -0.0221 0.0109 0.9993
8.750 1.0947 0.01433 0.00814 -0.0219 0.0104 0.9998
9.000 1.1170 0.01475 0.00859 -0.0211 0.0099 1.0000
9.250 1.1361 0.01522 0.00911 -0.0196 0.0094 1.0000
9.500 1.1544 0.01575 0.00970 -0.0180 0.0090 1.0000
9.750 1.1734 0.01617 0.01018 -0.0166 0.0087 1.0000
10.000 1.1916 0.01664 0.01072 -0.0150 0.0085 1.0000
10.250 1.2094 0.01711 0.01125 -0.0133 0.0083 1.0000
10.500 1.2262 0.01764 0.01185 -0.0115 0.0081 1.0000
10.750 1.2425 0.01817 0.01244 -0.0097 0.0078 1.0000
11.000 1.2582 0.01871 0.01306 -0.0077 0.0077 1.0000
11.250 1.2733 0.01926 0.01366 -0.0057 0.0074 1.0000
11.500 1.2870 0.01987 0.01433 -0.0035 0.0071 1.0000
11.750 1.2989 0.02057 0.01510 -0.0010 0.0070 1.0000
12.000 1.3069 0.02144 0.01607 0.0021 0.0067 1.0000
12.250 1.3141 0.02226 0.01698 0.0054 0.0067 1.0000
12.500 1.3185 0.02285 0.01766 0.0093 0.0066 1.0000
12.750 1.3211 0.02348 0.01838 0.0134 0.0065 1.0000
13.000 1.3229 0.02424 0.01923 0.0173 0.0065 1.0000
13.250 1.3259 0.02507 0.02016 0.0209 0.0064 1.0000
13.500 1.3287 0.02601 0.02119 0.0242 0.0064 1.0000
13.750 1.3305 0.02708 0.02237 0.0273 0.0063 1.0000
14.000 1.3334 0.02819 0.02357 0.0300 0.0063 1.0000
14.250 1.3336 0.02956 0.02505 0.0328 0.0062 1.0000
14.500 1.3352 0.03092 0.02652 0.0351 0.0061 1.0000
14.750 1.3338 0.03260 0.02832 0.0374 0.0061 1.0000
15.000 1.3307 0.03453 0.03038 0.0394 0.0060 1.0000
15.250 1.3251 0.03686 0.03283 0.0410 0.0060 1.0000
15.500 1.3190 0.03944 0.03553 0.0421 0.0059 1.0000
15.750 1.3118 0.04246 0.03868 0.0425 0.0059 1.0000
16.000 1.2933 0.04738 0.04377 0.0415 0.0059 1.0000
16.250 1.2863 0.05155 0.04807 0.0397 0.0058 1.0000
16.500 1.2593 0.05988 0.05660 0.0347 0.0059 1.0000
16.750 1.2338 0.06902 0.06592 0.0290 0.0059 1.0000
17.000 1.1915 0.08103 0.07812 0.0224 0.0060 1.0000
17.250 1.1519 0.09204 0.08925 0.0168 0.0060 1.0000
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