OAF102 AIRFOIL (oaf102-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: OAF102 AIRFOIL (oaf102-il) Reynolds number: 1,000,000 Max Cl/Cd: 92 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf102-il-1000000-n5.txt Download as CSV file: xf-oaf102-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: OAF102 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9627 0.07975 0.07728 -0.0225 1.0000 0.0066
-14.000 -1.0014 0.06940 0.06683 -0.0294 1.0000 0.0066
-13.750 -1.0457 0.05845 0.05575 -0.0372 1.0000 0.0065
-13.500 -1.0869 0.04592 0.04304 -0.0496 1.0000 0.0064
-13.250 -1.0848 0.03291 0.02970 -0.0702 1.0000 0.0065
-13.000 -1.0582 0.02789 0.02441 -0.0796 1.0000 0.0066
-12.750 -1.0326 0.02574 0.02209 -0.0830 1.0000 0.0067
-12.500 -1.0061 0.02411 0.02032 -0.0854 1.0000 0.0067
-12.250 -0.9792 0.02232 0.01838 -0.0880 1.0000 0.0070
-12.000 -0.9514 0.02094 0.01688 -0.0900 1.0000 0.0073
-11.750 -0.9232 0.01990 0.01574 -0.0915 1.0000 0.0076
-11.500 -0.8946 0.01902 0.01479 -0.0928 1.0000 0.0078
-11.250 -0.8657 0.01821 0.01390 -0.0940 1.0000 0.0081
-10.750 -0.8054 0.01677 0.01226 -0.0967 0.9678 0.0087
-10.500 -0.7777 0.01620 0.01157 -0.0972 0.9548 0.0090
-10.250 -0.7503 0.01568 0.01095 -0.0976 0.9432 0.0092
-10.000 -0.7220 0.01503 0.01020 -0.0983 0.9334 0.0097
-9.750 -0.6938 0.01450 0.00958 -0.0988 0.9240 0.0102
-9.500 -0.6653 0.01405 0.00905 -0.0993 0.9141 0.0107
-9.250 -0.6364 0.01364 0.00856 -0.0998 0.9048 0.0113
-9.000 -0.6076 0.01327 0.00810 -0.1002 0.8958 0.0118
-8.750 -0.5783 0.01293 0.00767 -0.1008 0.8863 0.0123
-8.500 -0.5488 0.01250 0.00717 -0.1014 0.8770 0.0132
-8.250 -0.5194 0.01217 0.00677 -0.1019 0.8670 0.0142
-8.000 -0.4898 0.01189 0.00641 -0.1024 0.8576 0.0153
-7.750 -0.4602 0.01162 0.00606 -0.1029 0.8485 0.0162
-7.500 -0.4302 0.01130 0.00569 -0.1035 0.8387 0.0177
-7.250 -0.4004 0.01104 0.00537 -0.1041 0.8293 0.0192
-7.000 -0.3707 0.01084 0.00509 -0.1045 0.8198 0.0203
-6.750 -0.3406 0.01056 0.00478 -0.1051 0.8108 0.0229
-6.500 -0.3106 0.01036 0.00451 -0.1056 0.8021 0.0252
-6.250 -0.2806 0.01015 0.00426 -0.1061 0.7930 0.0279
-6.000 -0.2505 0.00994 0.00402 -0.1067 0.7849 0.0314
-5.750 -0.2205 0.00976 0.00379 -0.1072 0.7766 0.0355
-5.500 -0.1904 0.00957 0.00358 -0.1077 0.7688 0.0401
-5.250 -0.1602 0.00940 0.00338 -0.1082 0.7605 0.0465
-5.000 -0.1301 0.00921 0.00319 -0.1087 0.7526 0.0548
-4.750 -0.0999 0.00905 0.00301 -0.1093 0.7442 0.0650
-4.500 -0.0697 0.00886 0.00284 -0.1098 0.7358 0.0786
-4.250 -0.0395 0.00871 0.00270 -0.1103 0.7282 0.0923
-4.000 -0.0093 0.00855 0.00256 -0.1109 0.7210 0.1080
-3.750 0.0208 0.00841 0.00244 -0.1114 0.7147 0.1240
-3.500 0.0509 0.00828 0.00234 -0.1119 0.7094 0.1407
-3.250 0.0810 0.00815 0.00225 -0.1123 0.7037 0.1589
-3.000 0.1110 0.00806 0.00218 -0.1128 0.6984 0.1756
-2.750 0.1409 0.00799 0.00212 -0.1132 0.6933 0.1885
-2.500 0.1708 0.00792 0.00206 -0.1136 0.6877 0.2010
-2.250 0.2007 0.00786 0.00202 -0.1139 0.6824 0.2141
-2.000 0.2306 0.00779 0.00198 -0.1143 0.6770 0.2272
-1.750 0.2604 0.00774 0.00194 -0.1147 0.6718 0.2404
-1.500 0.2902 0.00770 0.00192 -0.1151 0.6671 0.2528
-1.250 0.3200 0.00766 0.00191 -0.1154 0.6614 0.2661
-1.000 0.3497 0.00764 0.00189 -0.1158 0.6549 0.2796
-0.750 0.3795 0.00761 0.00189 -0.1161 0.6490 0.2925
-0.250 0.4388 0.00759 0.00191 -0.1167 0.6378 0.3206
0.000 0.4685 0.00757 0.00193 -0.1171 0.6323 0.3334
0.250 0.4981 0.00756 0.00196 -0.1174 0.6266 0.3482
0.500 0.5277 0.00756 0.00199 -0.1177 0.6211 0.3612
0.750 0.5573 0.00757 0.00203 -0.1179 0.6152 0.3708
1.000 0.5868 0.00760 0.00207 -0.1182 0.6091 0.3805
1.250 0.6163 0.00761 0.00212 -0.1185 0.6033 0.3897
1.750 0.6752 0.00767 0.00223 -0.1190 0.5899 0.4086
2.000 0.7044 0.00774 0.00229 -0.1193 0.5767 0.4178
2.250 0.7332 0.00797 0.00237 -0.1195 0.5320 0.4280
2.500 0.7616 0.00837 0.00252 -0.1198 0.4674 0.4393
2.750 0.7900 0.00873 0.00270 -0.1201 0.4177 0.4509
3.000 0.8182 0.00919 0.00294 -0.1204 0.3578 0.4633
3.250 0.8455 0.00991 0.00329 -0.1207 0.2711 0.4774
3.500 0.8727 0.01064 0.00369 -0.1210 0.1893 0.4926
4.000 0.9274 0.01173 0.00440 -0.1214 0.0843 0.5308
4.250 0.9552 0.01205 0.00467 -0.1215 0.0636 0.5507
4.500 0.9832 0.01230 0.00494 -0.1217 0.0515 0.5740
4.750 1.0111 0.01254 0.00520 -0.1218 0.0428 0.6037
5.000 1.0391 0.01276 0.00549 -0.1220 0.0356 0.6495
5.250 1.0672 0.01280 0.00582 -0.1222 0.0316 0.7665
5.500 1.0878 0.01263 0.00602 -0.1205 0.0279 1.0000
5.750 1.1152 0.01291 0.00630 -0.1205 0.0256 1.0000
6.000 1.1422 0.01326 0.00661 -0.1205 0.0226 1.0000
6.250 1.1693 0.01356 0.00692 -0.1204 0.0209 1.0000
6.500 1.1960 0.01389 0.00725 -0.1203 0.0193 1.0000
6.750 1.2224 0.01426 0.00761 -0.1201 0.0178 1.0000
7.000 1.2487 0.01463 0.00799 -0.1199 0.0166 1.0000
7.250 1.2749 0.01498 0.00836 -0.1198 0.0156 1.0000
7.500 1.3007 0.01536 0.00874 -0.1195 0.0146 1.0000
7.750 1.3260 0.01579 0.00918 -0.1192 0.0137 1.0000
8.000 1.3508 0.01627 0.00967 -0.1188 0.0129 1.0000
8.250 1.3757 0.01668 0.01012 -0.1184 0.0124 1.0000
8.500 1.4003 0.01712 0.01060 -0.1180 0.0119 1.0000
8.750 1.4243 0.01759 0.01109 -0.1175 0.0114 1.0000
9.000 1.4479 0.01809 0.01161 -0.1169 0.0109 1.0000
9.250 1.4708 0.01863 0.01217 -0.1162 0.0104 1.0000
9.500 1.4922 0.01932 0.01289 -0.1153 0.0097 1.0000
9.750 1.5146 0.01983 0.01345 -0.1146 0.0095 1.0000
10.000 1.5362 0.02039 0.01407 -0.1137 0.0092 1.0000
10.250 1.5569 0.02100 0.01473 -0.1127 0.0090 1.0000
10.500 1.5767 0.02163 0.01541 -0.1116 0.0087 1.0000
10.750 1.5956 0.02229 0.01611 -0.1103 0.0084 1.0000
11.000 1.6133 0.02298 0.01686 -0.1089 0.0081 1.0000
11.250 1.6297 0.02372 0.01765 -0.1072 0.0079 1.0000
11.500 1.6442 0.02454 0.01852 -0.1053 0.0077 1.0000
11.750 1.6562 0.02549 0.01953 -0.1031 0.0074 1.0000
12.000 1.6614 0.02668 0.02080 -0.0999 0.0072 1.0000
12.250 1.6691 0.02780 0.02200 -0.0973 0.0071 1.0000
12.500 1.6781 0.02895 0.02324 -0.0951 0.0070 1.0000
12.750 1.6872 0.03018 0.02455 -0.0931 0.0069 1.0000
13.000 1.6962 0.03149 0.02595 -0.0913 0.0068 1.0000
13.250 1.7042 0.03295 0.02750 -0.0896 0.0066 1.0000
13.500 1.7119 0.03449 0.02913 -0.0880 0.0065 1.0000
13.750 1.7191 0.03613 0.03085 -0.0865 0.0064 1.0000
14.000 1.7251 0.03793 0.03275 -0.0851 0.0062 1.0000
14.250 1.7306 0.03986 0.03476 -0.0838 0.0061 1.0000
14.500 1.7352 0.04192 0.03692 -0.0826 0.0060 1.0000
14.750 1.7388 0.04413 0.03922 -0.0815 0.0059 1.0000
15.000 1.7412 0.04653 0.04171 -0.0805 0.0058 1.0000
15.250 1.7430 0.04905 0.04433 -0.0797 0.0057 1.0000
15.500 1.7435 0.05177 0.04715 -0.0789 0.0057 1.0000
15.750 1.7425 0.05472 0.05020 -0.0783 0.0056 1.0000
16.000 1.7401 0.05791 0.05349 -0.0778 0.0055 1.0000
16.250 1.7359 0.06142 0.05712 -0.0775 0.0054 1.0000
16.500 1.7300 0.06528 0.06110 -0.0775 0.0053 1.0000
16.750 1.7230 0.06944 0.06538 -0.0777 0.0053 1.0000
17.000 1.7135 0.07414 0.07021 -0.0782 0.0052 1.0000
17.250 1.7015 0.07937 0.07557 -0.0792 0.0051 1.0000
17.500 1.6871 0.08513 0.08148 -0.0805 0.0051 1.0000
17.750 1.6729 0.09112 0.08760 -0.0822 0.0051 1.0000
18.000 1.6612 0.09687 0.09350 -0.0841 0.0050 1.0000
18.250 1.6464 0.10329 0.10006 -0.0864 0.0050 1.0000
18.500 1.6302 0.11015 0.10706 -0.0891 0.0050 1.0000
18.750 1.6118 0.11768 0.11474 -0.0925 0.0050 1.0000
19.000 1.5919 0.12576 0.12297 -0.0964 0.0050 1.0000
19.250 1.5702 0.13449 0.13185 -0.1010 0.0050 1.0000
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