CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: CURTISS CR-1 AIRFOIL (cr1-il) Reynolds number: 500,000 Max Cl/Cd: 109.47 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cr1-il-500000.txt Download as CSV file: xf-cr1-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2925 0.12419 0.12178 -0.0431 1.0000 0.0379
-11.750 -0.2904 0.12156 0.11917 -0.0432 1.0000 0.0391
-11.250 -0.6446 0.03331 0.02993 -0.1114 0.9714 0.0359
-11.000 -0.6274 0.03046 0.02692 -0.1133 0.9655 0.0366
-10.750 -0.5983 0.02954 0.02598 -0.1149 0.9605 0.0374
-10.500 -0.5693 0.02795 0.02424 -0.1171 0.9563 0.0382
-10.250 -0.5463 0.02635 0.02245 -0.1180 0.9482 0.0390
-10.000 -0.5198 0.02476 0.02062 -0.1193 0.9417 0.0399
-9.750 -0.4987 0.02332 0.01892 -0.1192 0.9323 0.0406
-9.500 -0.4739 0.02208 0.01740 -0.1196 0.9246 0.0412
-9.250 -0.4551 0.02106 0.01615 -0.1184 0.9139 0.0416
-9.000 -0.4386 0.01919 0.01406 -0.1173 0.9045 0.0425
-8.750 -0.4169 0.01856 0.01337 -0.1163 0.8951 0.0434
-8.500 -0.3945 0.01797 0.01268 -0.1154 0.8866 0.0441
-8.250 -0.3724 0.01735 0.01193 -0.1144 0.8781 0.0449
-8.000 -0.3499 0.01676 0.01120 -0.1135 0.8701 0.0457
-7.750 -0.3273 0.01618 0.01047 -0.1125 0.8619 0.0465
-7.500 -0.3037 0.01567 0.00982 -0.1116 0.8548 0.0474
-7.250 -0.2800 0.01524 0.00927 -0.1107 0.8473 0.0481
-7.000 -0.2573 0.01438 0.00827 -0.1098 0.8412 0.0494
-6.750 -0.2342 0.01392 0.00778 -0.1089 0.8339 0.0507
-6.500 -0.2093 0.01355 0.00735 -0.1082 0.8279 0.0519
-6.250 -0.1840 0.01322 0.00693 -0.1076 0.8224 0.0533
-6.000 -0.1591 0.01288 0.00653 -0.1069 0.8162 0.0547
-5.750 -0.1329 0.01264 0.00616 -0.1064 0.8110 0.0560
-5.500 -0.1089 0.01209 0.00560 -0.1056 0.8060 0.0585
-5.250 -0.0833 0.01188 0.00538 -0.1050 0.8006 0.0611
-5.000 -0.0569 0.01168 0.00510 -0.1046 0.7957 0.0639
-4.750 -0.0309 0.01135 0.00474 -0.1041 0.7914 0.0677
-4.500 -0.0050 0.01119 0.00459 -0.1035 0.7864 0.0721
-4.250 0.0211 0.01098 0.00435 -0.1030 0.7817 0.0774
-4.000 0.0485 0.01091 0.00425 -0.1028 0.7774 0.0833
-3.750 0.0749 0.01077 0.00409 -0.1023 0.7729 0.0892
-3.500 0.1013 0.01070 0.00403 -0.1019 0.7674 0.0949
-3.250 0.1285 0.01064 0.00389 -0.1015 0.7622 0.0995
-3.000 0.1546 0.01047 0.00373 -0.1010 0.7571 0.1055
-2.750 0.1809 0.01040 0.00364 -0.1005 0.7518 0.1103
-2.500 0.2073 0.01027 0.00348 -0.1001 0.7468 0.1155
-2.250 0.2343 0.01019 0.00339 -0.0997 0.7419 0.1211
-2.000 0.2603 0.01012 0.00331 -0.0992 0.7366 0.1258
-1.750 0.2863 0.00998 0.00318 -0.0986 0.7314 0.1316
-1.500 0.3138 0.00995 0.00313 -0.0984 0.7268 0.1384
-1.250 0.3396 0.00987 0.00307 -0.0978 0.7219 0.1448
-1.000 0.3656 0.00978 0.00302 -0.0973 0.7166 0.1523
-0.750 0.3925 0.00974 0.00294 -0.0969 0.7117 0.1596
-0.500 0.4187 0.00968 0.00293 -0.0964 0.7065 0.1693
-0.250 0.4443 0.00961 0.00289 -0.0957 0.7007 0.1801
0.000 0.4709 0.00958 0.00284 -0.0953 0.6949 0.1920
0.250 0.4960 0.00952 0.00283 -0.0945 0.6874 0.2051
0.500 0.5210 0.00944 0.00277 -0.0938 0.6793 0.2179
0.750 0.5461 0.00938 0.00273 -0.0930 0.6715 0.2297
1.000 0.5714 0.00934 0.00270 -0.0923 0.6639 0.2415
1.250 0.5966 0.00929 0.00268 -0.0916 0.6568 0.2552
1.500 0.6211 0.00921 0.00267 -0.0908 0.6482 0.2703
1.750 0.6458 0.00916 0.00265 -0.0900 0.6404 0.2893
2.000 0.6696 0.00905 0.00266 -0.0890 0.6312 0.3212
2.250 0.6865 0.00848 0.00271 -0.0869 0.6221 0.5375
2.500 0.8497 0.00790 0.00307 -0.1163 0.5993 1.0000
2.750 0.8715 0.00800 0.00309 -0.1149 0.5834 1.0000
3.000 0.8920 0.00815 0.00314 -0.1132 0.5645 1.0000
3.250 0.9119 0.00833 0.00321 -0.1115 0.5428 1.0000
3.500 0.9311 0.00855 0.00331 -0.1097 0.5202 1.0000
3.750 0.9492 0.00882 0.00345 -0.1076 0.4974 1.0000
4.000 0.9674 0.00910 0.00361 -0.1056 0.4745 1.0000
4.250 0.9848 0.00940 0.00380 -0.1035 0.4529 1.0000
4.500 1.0020 0.00972 0.00400 -0.1014 0.4329 1.0000
4.750 1.0195 0.01002 0.00421 -0.0993 0.4141 1.0000
5.000 1.0366 0.01033 0.00443 -0.0971 0.3966 1.0000
5.250 1.0535 0.01064 0.00466 -0.0950 0.3802 1.0000
5.500 1.0699 0.01095 0.00490 -0.0927 0.3646 1.0000
5.750 1.0859 0.01127 0.00516 -0.0904 0.3500 1.0000
6.000 1.1010 0.01161 0.00542 -0.0879 0.3360 1.0000
6.250 1.1162 0.01194 0.00569 -0.0855 0.3225 1.0000
6.500 1.1314 0.01225 0.00596 -0.0830 0.3101 1.0000
6.750 1.1437 0.01257 0.00624 -0.0800 0.2983 1.0000
7.000 1.1531 0.01293 0.00653 -0.0764 0.2866 1.0000
7.250 1.1637 0.01328 0.00683 -0.0732 0.2749 1.0000
7.500 1.1768 0.01362 0.00714 -0.0704 0.2648 1.0000
7.750 1.1883 0.01404 0.00751 -0.0675 0.2558 1.0000
8.000 1.2030 0.01439 0.00786 -0.0652 0.2482 1.0000
8.250 1.2147 0.01488 0.00830 -0.0625 0.2413 1.0000
8.500 1.2311 0.01522 0.00868 -0.0606 0.2357 1.0000
8.750 1.2447 0.01570 0.00914 -0.0584 0.2295 1.0000
9.000 1.2591 0.01618 0.00961 -0.0563 0.2234 1.0000
9.250 1.2744 0.01663 0.01007 -0.0545 0.2173 1.0000
9.500 1.2868 0.01725 0.01065 -0.0523 0.2117 1.0000
9.750 1.3037 0.01767 0.01112 -0.0508 0.2069 1.0000
10.000 1.3187 0.01820 0.01166 -0.0491 0.2016 1.0000
10.250 1.3309 0.01890 0.01233 -0.0472 0.1966 1.0000
10.500 1.3476 0.01939 0.01288 -0.0458 0.1933 1.0000
10.750 1.3635 0.01993 0.01347 -0.0444 0.1891 1.0000
11.000 1.3768 0.02063 0.01417 -0.0427 0.1843 1.0000
11.250 1.3896 0.02139 0.01494 -0.0411 0.1803 1.0000
11.500 1.4066 0.02191 0.01553 -0.0399 0.1760 1.0000
11.750 1.4200 0.02266 0.01630 -0.0385 0.1708 1.0000
12.000 1.4314 0.02355 0.01720 -0.0369 0.1659 1.0000
12.250 1.4477 0.02417 0.01789 -0.0359 0.1606 1.0000
12.500 1.4587 0.02514 0.01885 -0.0344 0.1541 1.0000
12.750 1.4726 0.02594 0.01970 -0.0332 0.1468 1.0000
13.000 1.4822 0.02707 0.02080 -0.0318 0.1369 1.0000
13.250 1.4904 0.02833 0.02201 -0.0303 0.1198 1.0000
13.500 1.4814 0.03095 0.02435 -0.0278 0.0868 1.0000
13.750 1.4739 0.03357 0.02686 -0.0255 0.0670 1.0000
14.000 1.4495 0.03777 0.03080 -0.0227 0.0336 1.0000
14.250 1.4443 0.04052 0.03357 -0.0212 0.0279 1.0000
14.500 1.4441 0.04289 0.03601 -0.0201 0.0255 1.0000
14.750 1.4435 0.04537 0.03857 -0.0191 0.0239 1.0000
15.000 1.4382 0.04844 0.04172 -0.0182 0.0223 1.0000
15.250 1.4388 0.05099 0.04437 -0.0176 0.0216 1.0000
15.500 1.4371 0.05386 0.04735 -0.0171 0.0207 1.0000
15.750 1.4330 0.05710 0.05069 -0.0168 0.0200 1.0000
16.000 1.4271 0.06070 0.05439 -0.0167 0.0195 1.0000
16.250 1.4173 0.06490 0.05869 -0.0169 0.0189 1.0000
16.500 1.4046 0.06964 0.06355 -0.0174 0.0186 1.0000
16.750 1.3966 0.07390 0.06794 -0.0180 0.0182 1.0000
17.000 1.3883 0.07833 0.07248 -0.0188 0.0179 1.0000
17.250 1.3786 0.08302 0.07730 -0.0198 0.0177 1.0000
17.500 1.3672 0.08808 0.08247 -0.0210 0.0172 1.0000
17.750 1.3557 0.09325 0.08777 -0.0223 0.0171 1.0000
18.000 1.3423 0.09876 0.09340 -0.0239 0.0169 1.0000
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