CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: CURTISS CR-1 AIRFOIL (cr1-il) Reynolds number: 500,000 Max Cl/Cd: 89.77 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cr1-il-500000-n5.txt Download as CSV file: xf-cr1-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CURTISS CR-1 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7626 0.05565 0.05266 -0.0820 0.9997 0.0258
-13.000 -0.8317 0.03294 0.02933 -0.1078 0.9706 0.0257
-12.750 -0.8167 0.02994 0.02611 -0.1102 0.9614 0.0261
-12.500 -0.7911 0.02803 0.02408 -0.1127 0.9556 0.0266
-12.250 -0.7652 0.02657 0.02249 -0.1145 0.9478 0.0271
-12.000 -0.7359 0.02523 0.02101 -0.1166 0.9408 0.0276
-11.750 -0.7093 0.02403 0.01966 -0.1178 0.9322 0.0281
-11.250 -0.6591 0.02202 0.01730 -0.1190 0.9146 0.0294
-11.000 -0.6360 0.02117 0.01625 -0.1189 0.9062 0.0299
-10.750 -0.6151 0.02043 0.01534 -0.1181 0.8969 0.0303
-10.500 -0.5957 0.01956 0.01433 -0.1171 0.8884 0.0307
-10.250 -0.5765 0.01881 0.01349 -0.1160 0.8791 0.0312
-10.000 -0.5554 0.01821 0.01278 -0.1150 0.8712 0.0317
-9.750 -0.5337 0.01770 0.01217 -0.1141 0.8629 0.0323
-9.500 -0.5113 0.01721 0.01158 -0.1132 0.8556 0.0328
-9.250 -0.4893 0.01671 0.01097 -0.1123 0.8473 0.0334
-9.000 -0.4666 0.01622 0.01036 -0.1114 0.8396 0.0339
-8.750 -0.4439 0.01576 0.00979 -0.1104 0.8310 0.0345
-8.500 -0.4206 0.01534 0.00924 -0.1096 0.8233 0.0350
-8.250 -0.3969 0.01494 0.00873 -0.1088 0.8154 0.0354
-8.000 -0.3739 0.01447 0.00816 -0.1079 0.8083 0.0361
-7.750 -0.3505 0.01404 0.00767 -0.1070 0.8006 0.0369
-7.500 -0.3262 0.01371 0.00727 -0.1063 0.7934 0.0378
-7.250 -0.3015 0.01340 0.00689 -0.1056 0.7868 0.0386
-7.000 -0.2766 0.01309 0.00650 -0.1050 0.7805 0.0395
-6.750 -0.2515 0.01282 0.00613 -0.1043 0.7749 0.0404
-6.500 -0.2261 0.01256 0.00579 -0.1037 0.7690 0.0412
-6.250 -0.2009 0.01226 0.00544 -0.1031 0.7637 0.0423
-6.000 -0.1755 0.01200 0.00512 -0.1025 0.7591 0.0436
-5.750 -0.1496 0.01176 0.00486 -0.1021 0.7543 0.0454
-5.500 -0.1235 0.01156 0.00460 -0.1016 0.7495 0.0471
-5.250 -0.0975 0.01137 0.00435 -0.1011 0.7453 0.0490
-5.000 -0.0714 0.01115 0.00412 -0.1006 0.7413 0.0517
-4.750 -0.0450 0.01098 0.00391 -0.1002 0.7371 0.0547
-4.500 -0.0187 0.01080 0.00372 -0.0997 0.7329 0.0581
-4.250 0.0078 0.01066 0.00356 -0.0993 0.7290 0.0626
-4.000 0.0344 0.01053 0.00341 -0.0989 0.7254 0.0673
-3.750 0.0610 0.01041 0.00330 -0.0986 0.7212 0.0727
-3.500 0.0876 0.01030 0.00318 -0.0981 0.7165 0.0775
-3.250 0.1140 0.01022 0.00307 -0.0977 0.7114 0.0825
-3.000 0.1407 0.01015 0.00297 -0.0972 0.7062 0.0863
-2.750 0.1670 0.01004 0.00287 -0.0968 0.7008 0.0909
-2.500 0.1935 0.00998 0.00279 -0.0963 0.6959 0.0957
-2.250 0.2201 0.00993 0.00270 -0.0959 0.6910 0.0993
-2.000 0.2464 0.00982 0.00262 -0.0955 0.6857 0.1039
-1.750 0.2727 0.00976 0.00255 -0.0950 0.6803 0.1087
-1.500 0.2992 0.00973 0.00248 -0.0945 0.6756 0.1134
-1.250 0.3255 0.00963 0.00243 -0.0941 0.6704 0.1200
-1.000 0.3518 0.00957 0.00238 -0.0936 0.6648 0.1254
-0.500 0.4040 0.00946 0.00230 -0.0926 0.6535 0.1382
-0.250 0.4299 0.00942 0.00227 -0.0920 0.6468 0.1464
0.000 0.4557 0.00938 0.00225 -0.0914 0.6397 0.1558
0.250 0.4806 0.00936 0.00223 -0.0907 0.6289 0.1667
0.500 0.5054 0.00935 0.00221 -0.0899 0.6155 0.1772
0.750 0.5295 0.00936 0.00220 -0.0890 0.5999 0.1872
1.000 0.5536 0.00939 0.00220 -0.0880 0.5848 0.1956
1.250 0.5772 0.00944 0.00221 -0.0870 0.5688 0.2053
1.500 0.5998 0.00952 0.00224 -0.0859 0.5500 0.2142
2.000 0.6443 0.00975 0.00236 -0.0834 0.5123 0.2326
2.250 0.6659 0.00989 0.00244 -0.0820 0.4922 0.2424
2.500 0.6870 0.01004 0.00254 -0.0806 0.4723 0.2548
2.750 0.7076 0.01020 0.00266 -0.0791 0.4530 0.2727
3.000 0.7277 0.01033 0.00280 -0.0776 0.4351 0.2988
3.250 0.7470 0.01043 0.00295 -0.0759 0.4172 0.3469
3.750 0.9130 0.01017 0.00390 -0.1009 0.3604 1.0000
4.000 0.9323 0.01042 0.00407 -0.0991 0.3474 1.0000
4.250 0.9512 0.01067 0.00425 -0.0973 0.3348 1.0000
4.500 0.9700 0.01092 0.00443 -0.0955 0.3226 1.0000
4.750 0.9889 0.01115 0.00462 -0.0937 0.3116 1.0000
5.000 1.0070 0.01141 0.00482 -0.0918 0.3011 1.0000
5.250 1.0247 0.01168 0.00503 -0.0898 0.2905 1.0000
5.500 1.0426 0.01193 0.00525 -0.0878 0.2811 1.0000
5.750 1.0591 0.01221 0.00548 -0.0856 0.2720 1.0000
6.000 1.0763 0.01246 0.00571 -0.0836 0.2633 1.0000
6.250 1.0914 0.01275 0.00596 -0.0811 0.2554 1.0000
6.500 1.1052 0.01299 0.00618 -0.0783 0.2481 1.0000
6.750 1.1172 0.01329 0.00644 -0.0753 0.2411 1.0000
7.000 1.1314 0.01355 0.00670 -0.0727 0.2337 1.0000
7.250 1.1438 0.01391 0.00701 -0.0699 0.2255 1.0000
7.500 1.1589 0.01422 0.00731 -0.0676 0.2186 1.0000
7.750 1.1720 0.01462 0.00768 -0.0650 0.2112 1.0000
8.000 1.1885 0.01494 0.00801 -0.0631 0.2071 1.0000
8.250 1.2043 0.01529 0.00837 -0.0611 0.2029 1.0000
8.500 1.2197 0.01568 0.00877 -0.0591 0.1990 1.0000
8.750 1.2346 0.01613 0.00921 -0.0571 0.1949 1.0000
9.000 1.2508 0.01653 0.00964 -0.0554 0.1897 1.0000
9.250 1.2651 0.01705 0.01014 -0.0534 0.1839 1.0000
9.500 1.2800 0.01756 0.01065 -0.0517 0.1793 1.0000
9.750 1.2959 0.01804 0.01116 -0.0501 0.1745 1.0000
10.000 1.3097 0.01865 0.01175 -0.0483 0.1689 1.0000
10.250 1.3245 0.01922 0.01234 -0.0467 0.1642 1.0000
10.500 1.3404 0.01976 0.01292 -0.0452 0.1608 1.0000
10.750 1.3548 0.02040 0.01358 -0.0437 0.1564 1.0000
11.000 1.3679 0.02113 0.01431 -0.0420 0.1513 1.0000
11.250 1.3832 0.02176 0.01497 -0.0407 0.1463 1.0000
11.500 1.3954 0.02259 0.01579 -0.0391 0.1397 1.0000
11.750 1.4090 0.02336 0.01659 -0.0377 0.1325 1.0000
12.000 1.4196 0.02434 0.01754 -0.0361 0.1218 1.0000
12.250 1.4254 0.02569 0.01878 -0.0342 0.1023 1.0000
12.500 1.4271 0.02738 0.02035 -0.0321 0.0858 1.0000
12.750 1.4306 0.02900 0.02194 -0.0302 0.0744 1.0000
13.000 1.4318 0.03085 0.02374 -0.0283 0.0608 1.0000
13.250 1.4192 0.03390 0.02660 -0.0258 0.0330 1.0000
13.500 1.4158 0.03631 0.02901 -0.0240 0.0240 1.0000
13.750 1.4199 0.03815 0.03089 -0.0228 0.0214 1.0000
14.000 1.4225 0.04018 0.03298 -0.0216 0.0189 1.0000
14.250 1.4271 0.04209 0.03496 -0.0207 0.0178 1.0000
14.500 1.4315 0.04404 0.03698 -0.0198 0.0169 1.0000
14.750 1.4343 0.04621 0.03922 -0.0190 0.0161 1.0000
15.000 1.4345 0.04873 0.04182 -0.0183 0.0152 1.0000
15.250 1.4375 0.05102 0.04419 -0.0178 0.0147 1.0000
15.500 1.4387 0.05354 0.04681 -0.0174 0.0142 1.0000
15.750 1.4383 0.05634 0.04969 -0.0170 0.0137 1.0000
16.000 1.4369 0.05933 0.05278 -0.0169 0.0133 1.0000
16.250 1.4337 0.06264 0.05618 -0.0169 0.0129 1.0000
16.500 1.4287 0.06626 0.05989 -0.0171 0.0126 1.0000
16.750 1.4228 0.07009 0.06383 -0.0174 0.0123 1.0000
17.000 1.4179 0.07390 0.06775 -0.0180 0.0121 1.0000
17.250 1.4104 0.07818 0.07216 -0.0187 0.0120 1.0000
17.500 1.4029 0.08252 0.07661 -0.0196 0.0116 1.0000
17.750 1.3934 0.08724 0.08145 -0.0207 0.0115 1.0000
18.000 1.3826 0.09226 0.08659 -0.0220 0.0113 1.0000
18.250 1.3702 0.09759 0.09205 -0.0235 0.0111 1.0000
18.500 1.3599 0.10263 0.09719 -0.0251 0.0110 1.0000
18.750 1.3452 0.10851 0.10319 -0.0270 0.0109 1.0000
19.000 1.3315 0.11430 0.10910 -0.0290 0.0108 1.0000
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