CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: CURTISS CR-1 AIRFOIL (cr1-il) Reynolds number: 50,000 Max Cl/Cd: 32.44 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cr1-il-50000-n5.txt Download as CSV file: xf-cr1-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3432 0.11223 0.10548 -0.0367 1.0000 0.0983
-8.750 -0.3424 0.11003 0.10333 -0.0340 1.0000 0.0972
-8.500 -0.3486 0.10814 0.10150 -0.0317 1.0000 0.0958
-8.250 -0.3412 0.10442 0.09778 -0.0342 0.9952 0.0937
-8.000 -0.3338 0.10023 0.09359 -0.0383 0.9878 0.0919
-7.750 -0.3279 0.09627 0.08962 -0.0425 0.9803 0.0915
-7.500 -0.3245 0.09266 0.08601 -0.0461 0.9717 0.0920
-7.250 -0.3218 0.08891 0.08224 -0.0496 0.9627 0.0922
-7.000 -0.3123 0.08435 0.07764 -0.0549 0.9552 0.0925
-6.750 -0.3103 0.08024 0.07348 -0.0579 0.9456 0.0920
-6.500 -0.3000 0.07534 0.06848 -0.0629 0.9389 0.0916
-6.250 -0.2973 0.07130 0.06434 -0.0650 0.9298 0.0916
-6.000 -0.2821 0.06663 0.05948 -0.0695 0.9242 0.0933
-5.750 -0.2800 0.06280 0.05547 -0.0704 0.9153 0.0949
-5.500 -0.2662 0.05731 0.04960 -0.0740 0.9094 0.0967
-5.250 -0.2607 0.05260 0.04443 -0.0747 0.9019 0.0978
-5.000 -0.2456 0.04926 0.04076 -0.0752 0.8959 0.0996
-4.750 -0.2174 0.04839 0.03986 -0.0762 0.8920 0.1029
-4.500 -0.2067 0.04669 0.03793 -0.0747 0.8846 0.1060
-4.250 -0.1879 0.04361 0.03429 -0.0749 0.8792 0.1102
-4.000 -0.1605 0.04121 0.03145 -0.0760 0.8753 0.1144
-3.750 -0.1473 0.04081 0.03102 -0.0740 0.8679 0.1180
-3.500 -0.1238 0.03928 0.02907 -0.0739 0.8626 0.1248
-3.250 -0.0926 0.03812 0.02767 -0.0749 0.8588 0.1310
-3.000 -0.0789 0.03772 0.02715 -0.0728 0.8512 0.1368
-2.750 -0.0526 0.03673 0.02584 -0.0728 0.8458 0.1446
-2.500 -0.0190 0.03615 0.02511 -0.0739 0.8419 0.1539
-2.250 -0.0052 0.03576 0.02453 -0.0718 0.8337 0.1603
-2.000 0.0243 0.03536 0.02402 -0.0722 0.8283 0.1700
-1.750 0.0610 0.03476 0.02326 -0.0737 0.8246 0.1800
-1.500 0.0739 0.03469 0.02303 -0.0713 0.8151 0.1880
-1.250 0.1091 0.03420 0.02248 -0.0725 0.8104 0.1980
-1.000 0.1308 0.03408 0.02216 -0.0716 0.8025 0.2081
-0.750 0.1631 0.03378 0.02182 -0.0723 0.7962 0.2192
-0.500 0.2080 0.03325 0.02120 -0.0749 0.7924 0.2333
-0.250 0.2240 0.03338 0.02126 -0.0732 0.7820 0.2437
0.000 0.2665 0.03288 0.02071 -0.0753 0.7774 0.2601
0.250 0.2859 0.03296 0.02078 -0.0740 0.7676 0.2745
0.500 0.3245 0.03246 0.02036 -0.0755 0.7620 0.2961
0.750 0.3470 0.03240 0.02037 -0.0746 0.7528 0.3158
1.000 0.3818 0.03190 0.02003 -0.0755 0.7462 0.3479
1.500 0.4999 0.02979 0.01965 -0.0868 0.7323 1.0000
1.750 0.5411 0.02944 0.01903 -0.0881 0.7268 1.0000
2.000 0.5537 0.02990 0.01937 -0.0854 0.7142 1.0000
2.250 0.5793 0.02996 0.01929 -0.0845 0.7049 1.0000
2.500 0.6081 0.02987 0.01908 -0.0840 0.6957 1.0000
2.750 0.6247 0.03017 0.01931 -0.0818 0.6835 1.0000
3.000 0.6649 0.02964 0.01866 -0.0827 0.6767 1.0000
3.250 0.6780 0.03000 0.01897 -0.0800 0.6629 1.0000
3.500 0.6950 0.03021 0.01914 -0.0778 0.6497 1.0000
3.750 0.7186 0.03015 0.01903 -0.0765 0.6379 1.0000
4.000 0.7515 0.02968 0.01849 -0.0762 0.6278 1.0000
4.500 0.7834 0.02999 0.01876 -0.0714 0.5986 1.0000
4.750 0.8013 0.03005 0.01879 -0.0692 0.5841 1.0000
5.000 0.8208 0.03005 0.01877 -0.0672 0.5695 1.0000
5.250 0.8417 0.03003 0.01872 -0.0655 0.5549 1.0000
5.500 0.8638 0.02999 0.01863 -0.0639 0.5400 1.0000
5.750 0.8863 0.02998 0.01856 -0.0624 0.5249 1.0000
6.000 0.9087 0.03001 0.01855 -0.0610 0.5093 1.0000
6.250 0.9310 0.03011 0.01859 -0.0595 0.4937 1.0000
6.500 0.9529 0.03030 0.01870 -0.0581 0.4783 1.0000
6.750 0.9737 0.03057 0.01891 -0.0567 0.4628 1.0000
7.000 0.9944 0.03092 0.01918 -0.0552 0.4478 1.0000
7.250 1.0156 0.03131 0.01948 -0.0539 0.4336 1.0000
7.500 1.0325 0.03192 0.02006 -0.0522 0.4195 1.0000
7.750 1.0476 0.03265 0.02077 -0.0504 0.4060 1.0000
8.000 1.0642 0.03337 0.02147 -0.0488 0.3935 1.0000
8.250 1.0846 0.03401 0.02206 -0.0476 0.3824 1.0000
8.500 1.1027 0.03477 0.02284 -0.0463 0.3718 1.0000
8.750 1.1178 0.03571 0.02382 -0.0447 0.3617 1.0000
9.000 1.1425 0.03628 0.02433 -0.0442 0.3525 1.0000
9.250 1.1521 0.03746 0.02563 -0.0421 0.3430 1.0000
9.500 1.1757 0.03815 0.02632 -0.0415 0.3352 1.0000
9.750 1.1862 0.03939 0.02771 -0.0397 0.3271 1.0000
10.000 1.2164 0.03994 0.02822 -0.0399 0.3207 1.0000
10.250 1.2201 0.04156 0.03005 -0.0375 0.3139 1.0000
10.500 1.2390 0.04253 0.03110 -0.0366 0.3076 1.0000
10.750 1.2543 0.04372 0.03239 -0.0354 0.3017 1.0000
11.000 1.2591 0.04540 0.03425 -0.0333 0.2958 1.0000
11.250 1.2809 0.04633 0.03525 -0.0327 0.2907 1.0000
11.500 1.2900 0.04796 0.03706 -0.0312 0.2860 1.0000
11.750 1.2848 0.05031 0.03963 -0.0287 0.2810 1.0000
12.000 1.3001 0.05145 0.04085 -0.0276 0.2756 1.0000
12.250 1.3064 0.05315 0.04267 -0.0261 0.2706 1.0000
12.500 1.2851 0.05671 0.04649 -0.0234 0.2656 1.0000
12.750 1.2928 0.05838 0.04826 -0.0221 0.2606 1.0000
13.000 1.3091 0.05949 0.04946 -0.0212 0.2559 1.0000
13.250 1.2541 0.06668 0.05693 -0.0192 0.2519 1.0000
13.500 1.2065 0.07449 0.06492 -0.0190 0.2471 1.0000
13.750 1.2434 0.07319 0.06373 -0.0178 0.2432 1.0000
14.000 1.0410 0.10629 0.09684 -0.0288 0.2304 1.0000
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Polar data table (+)
Polar graphs
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