ONERA NACA CAMBRE AIRFOIL (ncambre-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: ONERA NACA CAMBRE AIRFOIL (ncambre-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.02 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ncambre-il-1000000-n5.txt Download as CSV file: xf-ncambre-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ONERA NACA CAMBRE 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
------ -------- --------- --------- -------- -------- --------
-13.500 -1.0576 0.04456 0.04186 -0.0400 1.0000 0.0112
-13.250 -1.0897 0.03889 0.03584 -0.0392 1.0000 0.0113
-13.000 -1.1054 0.03544 0.03213 -0.0368 1.0000 0.0113
-12.750 -1.1131 0.03291 0.02938 -0.0337 1.0000 0.0114
-12.500 -1.1127 0.03081 0.02706 -0.0311 1.0000 0.0115
-12.250 -1.1056 0.02895 0.02501 -0.0291 1.0000 0.0116
-12.000 -1.0949 0.02736 0.02324 -0.0274 1.0000 0.0117
-11.750 -1.0814 0.02600 0.02171 -0.0259 1.0000 0.0117
-11.500 -1.0651 0.02490 0.02048 -0.0246 1.0000 0.0118
-11.250 -1.0474 0.02396 0.01942 -0.0235 1.0000 0.0119
-11.000 -1.0342 0.02231 0.01759 -0.0218 1.0000 0.0121
-10.750 -1.0164 0.02130 0.01648 -0.0205 1.0000 0.0122
-10.500 -0.9971 0.02049 0.01559 -0.0194 1.0000 0.0124
-10.250 -0.9772 0.01979 0.01482 -0.0183 1.0000 0.0125
-10.000 -0.9571 0.01915 0.01413 -0.0171 1.0000 0.0126
-9.750 -0.9372 0.01855 0.01346 -0.0159 1.0000 0.0127
-9.500 -0.9175 0.01799 0.01284 -0.0145 1.0000 0.0128
-9.250 -0.8980 0.01744 0.01224 -0.0131 1.0000 0.0129
-9.000 -0.8786 0.01690 0.01165 -0.0116 1.0000 0.0131
-8.750 -0.8544 0.01634 0.01102 -0.0112 0.9992 0.0132
-8.500 -0.8245 0.01573 0.01036 -0.0119 0.9972 0.0134
-8.250 -0.7939 0.01514 0.00971 -0.0128 0.9952 0.0136
-8.000 -0.7629 0.01457 0.00908 -0.0137 0.9932 0.0138
-7.750 -0.7330 0.01402 0.00848 -0.0144 0.9897 0.0140
-7.500 -0.7027 0.01352 0.00793 -0.0151 0.9861 0.0142
-7.250 -0.6723 0.01304 0.00740 -0.0159 0.9827 0.0144
-7.000 -0.6445 0.01262 0.00694 -0.0160 0.9769 0.0146
-6.750 -0.6145 0.01223 0.00651 -0.0165 0.9716 0.0147
-6.500 -0.5879 0.01181 0.00605 -0.0163 0.9638 0.0149
-6.250 -0.5609 0.01134 0.00556 -0.0162 0.9557 0.0153
-6.000 -0.5350 0.01102 0.00522 -0.0158 0.9444 0.0156
-5.750 -0.5088 0.01077 0.00495 -0.0154 0.9319 0.0160
-5.500 -0.4828 0.01055 0.00468 -0.0149 0.9186 0.0165
-5.250 -0.4570 0.01032 0.00440 -0.0144 0.9043 0.0169
-5.000 -0.4314 0.01010 0.00412 -0.0138 0.8882 0.0173
-4.750 -0.4055 0.00990 0.00385 -0.0133 0.8695 0.0177
-4.500 -0.3795 0.00974 0.00360 -0.0128 0.8479 0.0181
-4.250 -0.3533 0.00957 0.00334 -0.0123 0.8282 0.0184
-4.000 -0.3271 0.00936 0.00307 -0.0119 0.8096 0.0192
-3.750 -0.3004 0.00923 0.00288 -0.0116 0.7887 0.0199
-3.500 -0.2738 0.00914 0.00270 -0.0113 0.7641 0.0206
-3.250 -0.2469 0.00906 0.00253 -0.0110 0.7381 0.0214
-3.000 -0.2200 0.00900 0.00237 -0.0108 0.7127 0.0221
-2.750 -0.1931 0.00892 0.00221 -0.0105 0.6868 0.0235
-2.500 -0.1660 0.00887 0.00209 -0.0103 0.6635 0.0250
-2.250 -0.1386 0.00883 0.00197 -0.0101 0.6395 0.0264
-2.000 -0.1113 0.00879 0.00185 -0.0100 0.6128 0.0284
-1.750 -0.0841 0.00878 0.00176 -0.0098 0.5864 0.0310
-1.500 -0.0565 0.00874 0.00167 -0.0097 0.5667 0.0350
-1.250 -0.0289 0.00871 0.00160 -0.0096 0.5463 0.0407
-1.000 -0.0015 0.00867 0.00152 -0.0095 0.5231 0.0528
-0.250 0.0738 0.00732 0.00119 -0.0086 0.4746 0.4184
0.000 0.1002 0.00715 0.00116 -0.0084 0.4575 0.4812
0.250 0.1265 0.00701 0.00115 -0.0081 0.4373 0.5421
0.500 0.1526 0.00686 0.00116 -0.0078 0.4161 0.6095
0.750 0.1789 0.00678 0.00117 -0.0075 0.3943 0.6657
1.000 0.2056 0.00678 0.00120 -0.0073 0.3728 0.7002
1.250 0.2321 0.00677 0.00125 -0.0070 0.3546 0.7389
1.500 0.2587 0.00677 0.00131 -0.0066 0.3407 0.7772
1.750 0.2857 0.00680 0.00137 -0.0064 0.3254 0.8028
2.000 0.3125 0.00689 0.00144 -0.0061 0.3030 0.8245
2.250 0.3393 0.00700 0.00152 -0.0059 0.2820 0.8423
2.500 0.3663 0.00711 0.00160 -0.0056 0.2665 0.8600
2.750 0.3934 0.00720 0.00169 -0.0054 0.2546 0.8778
3.000 0.4200 0.00730 0.00179 -0.0051 0.2424 0.8948
3.750 0.5000 0.00770 0.00214 -0.0041 0.2062 0.9385
4.000 0.5275 0.00786 0.00226 -0.0040 0.1966 0.9475
4.250 0.5546 0.00802 0.00238 -0.0038 0.1867 0.9564
4.500 0.5839 0.00818 0.00251 -0.0041 0.1782 0.9632
4.750 0.6114 0.00836 0.00265 -0.0041 0.1687 0.9707
5.000 0.6427 0.00853 0.00280 -0.0049 0.1596 0.9749
5.250 0.6726 0.00873 0.00295 -0.0055 0.1505 0.9797
5.500 0.7023 0.00894 0.00311 -0.0060 0.1417 0.9843
5.750 0.7352 0.00913 0.00329 -0.0072 0.1350 0.9872
6.000 0.7672 0.00936 0.00348 -0.0083 0.1276 0.9901
6.250 0.7986 0.00956 0.00367 -0.0092 0.1215 0.9926
6.500 0.8296 0.00983 0.00389 -0.0101 0.1122 0.9945
6.750 0.8617 0.01006 0.00410 -0.0112 0.1053 0.9960
7.000 0.8932 0.01035 0.00433 -0.0122 0.0965 0.9977
7.250 0.9245 0.01064 0.00459 -0.0133 0.0899 0.9995
7.500 0.9502 0.01088 0.00481 -0.0130 0.0848 1.0000
7.750 0.9729 0.01109 0.00504 -0.0121 0.0815 1.0000
8.000 0.9954 0.01135 0.00528 -0.0112 0.0779 1.0000
8.250 1.0182 0.01160 0.00553 -0.0103 0.0747 1.0000
8.500 1.0413 0.01183 0.00577 -0.0095 0.0716 1.0000
8.750 1.0637 0.01214 0.00606 -0.0086 0.0666 1.0000
9.000 1.0869 0.01242 0.00635 -0.0079 0.0626 1.0000
9.250 1.1098 0.01276 0.00667 -0.0072 0.0573 1.0000
9.500 1.1327 0.01312 0.00701 -0.0065 0.0511 1.0000
10.000 1.1745 0.01427 0.00803 -0.0046 0.0312 1.0000
10.250 1.1958 0.01481 0.00855 -0.0038 0.0264 1.0000
10.500 1.2174 0.01531 0.00907 -0.0030 0.0230 1.0000
10.750 1.2393 0.01579 0.00956 -0.0023 0.0209 1.0000
11.000 1.2606 0.01630 0.01008 -0.0015 0.0191 1.0000
11.250 1.2817 0.01681 0.01062 -0.0007 0.0178 1.0000
11.500 1.3028 0.01730 0.01115 0.0001 0.0168 1.0000
11.750 1.3231 0.01784 0.01173 0.0010 0.0160 1.0000
12.000 1.3425 0.01844 0.01236 0.0020 0.0152 1.0000
12.250 1.3614 0.01904 0.01300 0.0030 0.0146 1.0000
12.500 1.3805 0.01959 0.01362 0.0040 0.0143 1.0000
12.750 1.3985 0.02019 0.01427 0.0051 0.0138 1.0000
13.000 1.4150 0.02083 0.01496 0.0064 0.0134 1.0000
13.250 1.4284 0.02151 0.01570 0.0082 0.0129 1.0000
13.500 1.4403 0.02229 0.01653 0.0101 0.0125 1.0000
13.750 1.4509 0.02317 0.01748 0.0119 0.0122 1.0000
14.000 1.4597 0.02422 0.01860 0.0138 0.0118 1.0000
14.250 1.4698 0.02522 0.01967 0.0153 0.0116 1.0000
14.500 1.4797 0.02630 0.02083 0.0166 0.0114 1.0000
14.750 1.4883 0.02753 0.02214 0.0178 0.0112 1.0000
15.000 1.4957 0.02894 0.02364 0.0188 0.0110 1.0000
15.250 1.5020 0.03054 0.02534 0.0196 0.0108 1.0000
15.500 1.5070 0.03239 0.02727 0.0201 0.0106 1.0000
15.750 1.5104 0.03451 0.02948 0.0203 0.0104 1.0000
16.000 1.5121 0.03697 0.03204 0.0202 0.0102 1.0000
16.250 1.5117 0.03983 0.03499 0.0197 0.0100 1.0000
16.500 1.5089 0.04318 0.03844 0.0188 0.0098 1.0000
16.750 1.5026 0.04713 0.04251 0.0174 0.0096 1.0000
17.000 1.4927 0.05177 0.04728 0.0155 0.0095 1.0000
17.250 1.4786 0.05719 0.05283 0.0132 0.0094 1.0000
17.500 1.4600 0.06340 0.05918 0.0104 0.0093 1.0000
17.750 1.4375 0.07034 0.06628 0.0072 0.0093 1.0000
18.000 1.4107 0.07813 0.07422 0.0036 0.0093 1.0000
18.250 1.3815 0.08651 0.08275 -0.0003 0.0093 1.0000
18.500 1.3490 0.09557 0.09197 -0.0045 0.0094 1.0000
18.750 1.3166 0.10484 0.10139 -0.0089 0.0094 1.0000
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