CURTISS CR-1 AIRFOIL (cr1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: CURTISS CR-1 AIRFOIL (cr1-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.3 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-cr1-il-1000000-n5.txt Download as CSV file: xf-cr1-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.6923 0.08825 0.08600 -0.0654 1.0000 0.0212
-15.000 -1.0499 0.03435 0.03138 -0.1060 0.9856 0.0192
-14.750 -1.0461 0.02846 0.02521 -0.1093 0.9777 0.0195
-14.500 -1.0256 0.02646 0.02307 -0.1107 0.9712 0.0199
-14.250 -1.0004 0.02495 0.02145 -0.1123 0.9653 0.0204
-14.000 -0.9704 0.02362 0.02000 -0.1144 0.9595 0.0209
-13.750 -0.9373 0.02248 0.01874 -0.1169 0.9536 0.0214
-13.500 -0.9042 0.02149 0.01761 -0.1192 0.9444 0.0217
-13.250 -0.8746 0.02040 0.01639 -0.1208 0.9334 0.0221
-13.000 -0.8494 0.01953 0.01540 -0.1213 0.9212 0.0226
-12.750 -0.8271 0.01888 0.01465 -0.1208 0.9104 0.0230
-12.500 -0.8057 0.01834 0.01402 -0.1201 0.9014 0.0235
-12.250 -0.7845 0.01783 0.01340 -0.1192 0.8927 0.0239
-12.000 -0.7633 0.01733 0.01282 -0.1182 0.8852 0.0243
-11.750 -0.7418 0.01687 0.01226 -0.1172 0.8772 0.0247
-11.500 -0.7197 0.01645 0.01175 -0.1163 0.8698 0.0251
-11.250 -0.6975 0.01605 0.01125 -0.1154 0.8613 0.0254
-11.000 -0.6751 0.01564 0.01074 -0.1145 0.8536 0.0257
-10.750 -0.6530 0.01521 0.01021 -0.1135 0.8453 0.0261
-10.500 -0.6314 0.01471 0.00964 -0.1125 0.8375 0.0267
-10.250 -0.6085 0.01432 0.00918 -0.1116 0.8286 0.0273
-10.000 -0.5853 0.01396 0.00875 -0.1108 0.8198 0.0277
-9.750 -0.5620 0.01363 0.00833 -0.1099 0.8099 0.0281
-9.500 -0.5381 0.01332 0.00794 -0.1091 0.8005 0.0285
-9.250 -0.5142 0.01304 0.00757 -0.1083 0.7914 0.0290
-9.000 -0.4897 0.01276 0.00721 -0.1076 0.7831 0.0294
-8.750 -0.4655 0.01249 0.00685 -0.1068 0.7753 0.0298
-8.500 -0.4406 0.01223 0.00652 -0.1061 0.7680 0.0301
-8.250 -0.4157 0.01200 0.00621 -0.1055 0.7608 0.0304
-8.000 -0.3912 0.01166 0.00580 -0.1047 0.7551 0.0310
-7.750 -0.3663 0.01136 0.00545 -0.1041 0.7495 0.0316
-7.500 -0.3411 0.01112 0.00515 -0.1035 0.7441 0.0322
-7.250 -0.3153 0.01089 0.00488 -0.1030 0.7395 0.0329
-7.000 -0.2893 0.01068 0.00463 -0.1025 0.7350 0.0337
-6.750 -0.2632 0.01050 0.00440 -0.1020 0.7307 0.0344
-6.250 -0.2106 0.01015 0.00395 -0.1011 0.7230 0.0355
-6.000 -0.1843 0.00994 0.00371 -0.1007 0.7194 0.0364
-5.750 -0.1580 0.00974 0.00350 -0.1002 0.7157 0.0377
-5.500 -0.1316 0.00959 0.00331 -0.0998 0.7120 0.0389
-5.250 -0.1050 0.00944 0.00313 -0.0994 0.7087 0.0402
-5.000 -0.0780 0.00930 0.00298 -0.0990 0.7056 0.0416
-4.750 -0.0513 0.00912 0.00280 -0.0987 0.7021 0.0443
-4.500 -0.0246 0.00899 0.00266 -0.0983 0.6983 0.0469
-4.250 0.0018 0.00888 0.00252 -0.0978 0.6940 0.0501
-4.000 0.0286 0.00874 0.00239 -0.0974 0.6895 0.0541
-3.750 0.0553 0.00862 0.00228 -0.0971 0.6843 0.0584
-3.500 0.0819 0.00852 0.00218 -0.0966 0.6795 0.0635
-3.250 0.1085 0.00843 0.00209 -0.0962 0.6750 0.0684
-3.000 0.1356 0.00834 0.00201 -0.0959 0.6704 0.0738
-2.750 0.1623 0.00825 0.00193 -0.0955 0.6651 0.0785
-2.500 0.1888 0.00820 0.00187 -0.0951 0.6602 0.0831
-2.250 0.2162 0.00815 0.00181 -0.0948 0.6558 0.0860
-2.000 0.2431 0.00807 0.00175 -0.0944 0.6508 0.0903
-1.750 0.2697 0.00802 0.00170 -0.0940 0.6458 0.0944
-1.500 0.2966 0.00799 0.00165 -0.0936 0.6402 0.0978
-1.250 0.3235 0.00794 0.00161 -0.0933 0.6338 0.1015
-1.000 0.3494 0.00791 0.00157 -0.0927 0.6268 0.1067
-0.750 0.3760 0.00788 0.00153 -0.0923 0.6174 0.1107
-0.500 0.4014 0.00788 0.00150 -0.0916 0.6039 0.1158
-0.250 0.4256 0.00791 0.00148 -0.0907 0.5837 0.1219
0.000 0.4493 0.00799 0.00148 -0.0897 0.5616 0.1267
0.250 0.4731 0.00806 0.00150 -0.0888 0.5407 0.1353
0.750 0.5203 0.00825 0.00159 -0.0868 0.5005 0.1550
1.000 0.5437 0.00836 0.00165 -0.0859 0.4811 0.1667
1.250 0.5672 0.00848 0.00172 -0.0849 0.4620 0.1757
1.500 0.5905 0.00861 0.00180 -0.0839 0.4433 0.1847
1.750 0.6139 0.00876 0.00188 -0.0829 0.4255 0.1913
2.000 0.6366 0.00890 0.00197 -0.0818 0.4066 0.2000
2.500 0.6822 0.00920 0.00217 -0.0797 0.3736 0.2152
2.750 0.7052 0.00934 0.00226 -0.0786 0.3592 0.2224
3.000 0.7280 0.00947 0.00237 -0.0776 0.3465 0.2310
3.250 0.7505 0.00961 0.00248 -0.0765 0.3342 0.2404
3.500 0.7727 0.00973 0.00259 -0.0753 0.3224 0.2551
3.750 0.7948 0.00983 0.00272 -0.0741 0.3116 0.2776
4.000 0.8161 0.00993 0.00285 -0.0728 0.3011 0.3094
4.250 0.8312 0.00965 0.00304 -0.0704 0.2914 0.5276
4.750 0.9855 0.00965 0.00393 -0.0927 0.2582 0.9959
5.000 1.0235 0.00989 0.00411 -0.0951 0.2480 0.9985
5.250 1.0576 0.01014 0.00430 -0.0967 0.2382 1.0000
5.500 1.0764 0.01038 0.00449 -0.0949 0.2291 1.0000
5.750 1.0953 0.01059 0.00467 -0.0931 0.2222 1.0000
6.000 1.1124 0.01085 0.00488 -0.0910 0.2126 1.0000
6.250 1.1303 0.01108 0.00507 -0.0890 0.2057 1.0000
6.500 1.1473 0.01132 0.00529 -0.0869 0.1992 1.0000
6.750 1.1643 0.01155 0.00550 -0.0848 0.1943 1.0000
7.000 1.1797 0.01173 0.00568 -0.0823 0.1908 1.0000
7.250 1.1927 0.01194 0.00588 -0.0793 0.1869 1.0000
7.500 1.2052 0.01219 0.00611 -0.0763 0.1822 1.0000
7.750 1.2198 0.01241 0.00634 -0.0738 0.1776 1.0000
8.000 1.2341 0.01269 0.00659 -0.0713 0.1724 1.0000
8.250 1.2485 0.01300 0.00688 -0.0689 0.1677 1.0000
8.500 1.2650 0.01326 0.00716 -0.0669 0.1650 1.0000
8.750 1.2816 0.01354 0.00745 -0.0649 0.1613 1.0000
9.000 1.2976 0.01387 0.00778 -0.0630 0.1576 1.0000
9.250 1.3129 0.01426 0.00815 -0.0610 0.1535 1.0000
9.500 1.3297 0.01460 0.00851 -0.0593 0.1496 1.0000
9.750 1.3455 0.01501 0.00892 -0.0575 0.1442 1.0000
10.000 1.3603 0.01549 0.00938 -0.0556 0.1392 1.0000
10.250 1.3767 0.01592 0.00982 -0.0540 0.1344 1.0000
10.500 1.3894 0.01655 0.01040 -0.0520 0.1247 1.0000
10.750 1.4013 0.01725 0.01105 -0.0499 0.1131 1.0000
11.250 1.4118 0.01954 0.01312 -0.0445 0.0786 1.0000
11.500 1.4202 0.02057 0.01412 -0.0424 0.0694 1.0000
11.750 1.4261 0.02180 0.01529 -0.0402 0.0554 1.0000
12.000 1.4162 0.02417 0.01747 -0.0365 0.0262 1.0000
12.250 1.4237 0.02542 0.01872 -0.0347 0.0207 1.0000
12.500 1.4330 0.02659 0.01990 -0.0332 0.0180 1.0000
12.750 1.4427 0.02775 0.02109 -0.0318 0.0163 1.0000
13.000 1.4523 0.02894 0.02232 -0.0304 0.0151 1.0000
13.250 1.4616 0.03018 0.02359 -0.0292 0.0138 1.0000
13.500 1.4705 0.03149 0.02494 -0.0280 0.0131 1.0000
13.750 1.4784 0.03291 0.02640 -0.0268 0.0124 1.0000
14.000 1.4870 0.03430 0.02785 -0.0257 0.0119 1.0000
14.250 1.4950 0.03577 0.02936 -0.0247 0.0115 1.0000
14.500 1.5024 0.03732 0.03096 -0.0237 0.0111 1.0000
14.750 1.5084 0.03904 0.03274 -0.0228 0.0106 1.0000
15.000 1.5131 0.04093 0.03468 -0.0219 0.0102 1.0000
15.250 1.5179 0.04284 0.03665 -0.0210 0.0098 1.0000
15.500 1.5233 0.04475 0.03861 -0.0203 0.0095 1.0000
15.750 1.5268 0.04689 0.04083 -0.0197 0.0093 1.0000
16.000 1.5304 0.04908 0.04308 -0.0191 0.0090 1.0000
16.250 1.5329 0.05142 0.04549 -0.0187 0.0087 1.0000
16.500 1.5341 0.05396 0.04810 -0.0183 0.0086 1.0000
16.750 1.5339 0.05673 0.05093 -0.0181 0.0082 1.0000
17.000 1.5323 0.05975 0.05403 -0.0180 0.0081 1.0000
17.250 1.5291 0.06304 0.05740 -0.0180 0.0079 1.0000
17.500 1.5255 0.06646 0.06091 -0.0182 0.0077 1.0000
17.750 1.5215 0.07000 0.06455 -0.0185 0.0077 1.0000
18.000 1.5168 0.07372 0.06836 -0.0190 0.0076 1.0000
18.250 1.5099 0.07782 0.07256 -0.0197 0.0074 1.0000
18.500 1.5038 0.08185 0.07668 -0.0204 0.0073 1.0000
18.750 1.4938 0.08653 0.08147 -0.0215 0.0073 1.0000
19.000 1.4832 0.09138 0.08642 -0.0227 0.0071 1.0000
19.250 1.4723 0.09634 0.09149 -0.0240 0.0070 1.0000
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