FX 61-147 AIRFOIL (fx61147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-147 AIRFOIL (fx61147-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.9 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61147-il-1000000.txt Download as CSV file: xf-fx61147-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-147 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2650 0.09807 0.09661 -0.0485 0.9974 0.0102
-11.000 -0.4558 0.04537 0.04371 -0.0669 0.9981 0.0063
-10.750 -0.4688 0.03816 0.03640 -0.0731 0.9966 0.0061
-10.500 -0.4973 0.02954 0.02754 -0.0796 0.9940 0.0060
-10.250 -0.5433 0.04800 0.04605 -0.0760 0.9956 0.0061
-10.000 -0.6042 0.03211 0.02928 -0.0876 0.9832 0.0058
-9.750 -0.5959 0.02598 0.02253 -0.0911 0.9773 0.0061
-9.500 -0.5680 0.02356 0.01982 -0.0938 0.9755 0.0063
-9.250 -0.5466 0.02256 0.01867 -0.0937 0.9691 0.0064
-9.000 -0.5256 0.01875 0.01442 -0.0952 0.9654 0.0067
-8.750 -0.4937 0.01761 0.01320 -0.0972 0.9634 0.0070
-8.500 -0.4707 0.01672 0.01223 -0.0969 0.9566 0.0072
-8.250 -0.4405 0.01603 0.01147 -0.0980 0.9526 0.0075
-8.000 -0.4070 0.01511 0.01047 -0.0998 0.9499 0.0077
-7.750 -0.3791 0.01431 0.00959 -0.1003 0.9425 0.0080
-7.500 -0.3420 0.01350 0.00870 -0.1028 0.9382 0.0084
-7.250 -0.3032 0.01281 0.00793 -0.1055 0.9322 0.0089
-7.000 -0.2627 0.01177 0.00678 -0.1091 0.9243 0.0097
-6.750 -0.2171 0.01131 0.00630 -0.1133 0.9161 0.0107
-6.500 -0.1687 0.01085 0.00575 -0.1182 0.9058 0.0119
-6.250 -0.1301 0.01025 0.00503 -0.1210 0.8901 0.0131
-6.000 -0.0980 0.00988 0.00457 -0.1224 0.8708 0.0145
-5.750 -0.0685 0.00968 0.00428 -0.1229 0.8498 0.0161
-5.500 -0.0419 0.00939 0.00385 -0.1229 0.8263 0.0178
-5.250 -0.0166 0.00922 0.00358 -0.1226 0.8023 0.0202
-5.000 0.0088 0.00913 0.00337 -0.1222 0.7791 0.0220
-4.750 0.0341 0.00891 0.00304 -0.1219 0.7579 0.0258
-4.500 0.0602 0.00880 0.00285 -0.1216 0.7375 0.0299
-4.250 0.0865 0.00856 0.00260 -0.1216 0.7174 0.0481
-3.750 0.1432 0.00750 0.00205 -0.1233 0.6813 0.2369
-3.500 0.1753 0.00672 0.00176 -0.1253 0.6656 0.4046
-3.250 0.2059 0.00640 0.00164 -0.1263 0.6510 0.4973
-3.000 0.2350 0.00632 0.00161 -0.1268 0.6370 0.5446
-2.750 0.2636 0.00633 0.00162 -0.1270 0.6239 0.5744
-2.500 0.2921 0.00638 0.00165 -0.1271 0.6116 0.6008
-2.250 0.3204 0.00647 0.00170 -0.1272 0.6002 0.6184
-2.000 0.3484 0.00658 0.00176 -0.1272 0.5891 0.6313
-1.500 0.4047 0.00678 0.00185 -0.1273 0.5690 0.6463
-1.250 0.4328 0.00689 0.00188 -0.1273 0.5603 0.6514
-1.000 0.4612 0.00699 0.00190 -0.1274 0.5512 0.6558
-0.750 0.4893 0.00705 0.00194 -0.1275 0.5431 0.6594
-0.500 0.5171 0.00715 0.00200 -0.1275 0.5351 0.6629
-0.250 0.5456 0.00723 0.00204 -0.1276 0.5281 0.6666
0.000 0.5737 0.00734 0.00208 -0.1278 0.5205 0.6699
0.250 0.6019 0.00740 0.00212 -0.1279 0.5136 0.6729
0.500 0.6297 0.00749 0.00219 -0.1279 0.5066 0.6757
0.750 0.6576 0.00758 0.00226 -0.1279 0.5001 0.6787
1.000 0.6857 0.00768 0.00232 -0.1280 0.4931 0.6816
1.250 0.7136 0.00778 0.00238 -0.1281 0.4864 0.6843
1.500 0.7418 0.00785 0.00243 -0.1283 0.4800 0.6868
1.750 0.7690 0.00796 0.00252 -0.1282 0.4736 0.6891
2.000 0.7972 0.00803 0.00260 -0.1283 0.4683 0.6914
2.250 0.8248 0.00813 0.00269 -0.1283 0.4624 0.6939
2.500 0.8524 0.00824 0.00278 -0.1284 0.4568 0.6965
2.750 0.8805 0.00833 0.00286 -0.1285 0.4509 0.6988
3.000 0.9078 0.00846 0.00296 -0.1285 0.4452 0.7010
3.250 0.9356 0.00852 0.00305 -0.1286 0.4402 0.7031
3.500 0.9630 0.00861 0.00316 -0.1286 0.4347 0.7051
3.750 0.9896 0.00876 0.00329 -0.1284 0.4289 0.7072
4.000 1.0174 0.00884 0.00340 -0.1285 0.4235 0.7094
4.250 1.0444 0.00897 0.00352 -0.1285 0.4177 0.7116
4.500 1.0715 0.00910 0.00365 -0.1284 0.4125 0.7136
4.750 1.0989 0.00921 0.00378 -0.1285 0.4063 0.7154
5.000 1.1250 0.00935 0.00391 -0.1283 0.3988 0.7175
5.250 1.1520 0.00945 0.00404 -0.1282 0.3905 0.7194
5.500 1.1781 0.00961 0.00420 -0.1280 0.3813 0.7212
5.750 1.2039 0.00978 0.00436 -0.1278 0.3718 0.7232
6.000 1.2303 0.00993 0.00453 -0.1276 0.3634 0.7253
6.250 1.2556 0.01014 0.00471 -0.1273 0.3521 0.7273
6.500 1.2804 0.01039 0.00492 -0.1270 0.3367 0.7290
6.750 1.3045 0.01068 0.00514 -0.1265 0.3177 0.7309
7.000 1.3276 0.01100 0.00540 -0.1258 0.2989 0.7328
7.250 1.3502 0.01136 0.00569 -0.1251 0.2793 0.7347
7.500 1.3722 0.01176 0.00603 -0.1242 0.2583 0.7366
7.750 1.3923 0.01229 0.00644 -0.1230 0.2325 0.7387
8.000 1.4108 0.01290 0.00691 -0.1216 0.2041 0.7406
8.250 1.4252 0.01376 0.00754 -0.1196 0.1655 0.7426
8.500 1.4367 0.01474 0.00829 -0.1171 0.1285 0.7444
8.750 1.4470 0.01559 0.00899 -0.1142 0.0994 0.7464
9.000 1.4557 0.01643 0.00971 -0.1111 0.0756 0.7483
9.250 1.4639 0.01731 0.01048 -0.1080 0.0558 0.7502
9.500 1.4731 0.01814 0.01124 -0.1051 0.0407 0.7523
9.750 1.4816 0.01900 0.01205 -0.1022 0.0294 0.7545
10.000 1.4907 0.01985 0.01288 -0.0995 0.0220 0.7566
10.250 1.4984 0.02078 0.01379 -0.0968 0.0155 0.7584
10.500 1.5035 0.02188 0.01487 -0.0937 0.0087 0.7602
10.750 1.5073 0.02310 0.01611 -0.0907 0.0048 0.7623
11.000 1.5152 0.02414 0.01723 -0.0884 0.0042 0.7645
11.250 1.5218 0.02531 0.01847 -0.0862 0.0038 0.7667
11.500 1.5273 0.02662 0.01987 -0.0839 0.0035 0.7690
11.750 1.5322 0.02806 0.02139 -0.0819 0.0033 0.7712
12.000 1.5378 0.02954 0.02295 -0.0801 0.0032 0.7732
12.250 1.5424 0.03119 0.02469 -0.0785 0.0031 0.7753
12.500 1.5459 0.03302 0.02662 -0.0770 0.0030 0.7775
12.750 1.5483 0.03506 0.02877 -0.0757 0.0030 0.7799
13.000 1.5500 0.03731 0.03111 -0.0747 0.0029 0.7824
13.250 1.5506 0.03979 0.03369 -0.0738 0.0028 0.7849
13.500 1.5505 0.04249 0.03649 -0.0732 0.0027 0.7872
13.750 1.5494 0.04543 0.03955 -0.0728 0.0027 0.7894
14.000 1.5474 0.04862 0.04285 -0.0726 0.0026 0.7918
14.250 1.5444 0.05207 0.04643 -0.0727 0.0026 0.7942
14.500 1.5404 0.05578 0.05024 -0.0730 0.0025 0.7966
14.750 1.5350 0.05980 0.05438 -0.0735 0.0025 0.7990
15.000 1.5286 0.06411 0.05881 -0.0742 0.0024 0.8014
15.250 1.5217 0.06864 0.06345 -0.0752 0.0024 0.8037
15.500 1.5134 0.07352 0.06846 -0.0764 0.0023 0.8061
15.750 1.5048 0.07860 0.07367 -0.0778 0.0023 0.8086
16.000 1.4939 0.08419 0.07939 -0.0796 0.0022 0.8110
16.250 1.4825 0.09000 0.08534 -0.0815 0.0022 0.8134
16.500 1.4724 0.09577 0.09123 -0.0836 0.0022 0.8157
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