GOE 398 AIRFOIL (goe398-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 398 AIRFOIL (goe398-il) Reynolds number: 500,000 Max Cl/Cd: 92.49 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe398-il-500000-n5.txt Download as CSV file: xf-goe398-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 398 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.8240 0.04704 0.04366 -0.0906 1.0000 0.0189
-14.000 -0.8683 0.03683 0.03317 -0.1007 0.9990 0.0188
-13.750 -0.8654 0.03290 0.02896 -0.1051 0.9923 0.0190
-13.500 -0.8524 0.03106 0.02703 -0.1062 0.9859 0.0193
-13.250 -0.8346 0.02952 0.02539 -0.1070 0.9799 0.0196
-13.000 -0.8132 0.02826 0.02404 -0.1078 0.9742 0.0199
-12.750 -0.7921 0.02718 0.02287 -0.1081 0.9681 0.0203
-12.500 -0.7702 0.02606 0.02162 -0.1085 0.9618 0.0207
-12.250 -0.7468 0.02489 0.02031 -0.1091 0.9561 0.0212
-12.000 -0.7225 0.02377 0.01900 -0.1097 0.9494 0.0218
-11.750 -0.6922 0.02258 0.01759 -0.1114 0.9452 0.0223
-11.500 -0.6653 0.02168 0.01664 -0.1121 0.9374 0.0227
-11.250 -0.6330 0.02089 0.01577 -0.1138 0.9310 0.0231
-11.000 -0.6023 0.02024 0.01504 -0.1149 0.9230 0.0237
-10.750 -0.5713 0.01954 0.01422 -0.1161 0.9145 0.0243
-10.500 -0.5437 0.01889 0.01344 -0.1165 0.9047 0.0249
-10.000 -0.4921 0.01768 0.01189 -0.1163 0.8837 0.0260
-9.750 -0.4686 0.01711 0.01126 -0.1157 0.8733 0.0265
-9.500 -0.4449 0.01669 0.01075 -0.1150 0.8627 0.0270
-9.250 -0.4215 0.01630 0.01028 -0.1142 0.8534 0.0276
-9.000 -0.3978 0.01594 0.00982 -0.1135 0.8444 0.0283
-8.750 -0.3746 0.01555 0.00932 -0.1126 0.8362 0.0289
-8.500 -0.3513 0.01516 0.00881 -0.1116 0.8279 0.0295
-8.250 -0.3278 0.01478 0.00833 -0.1107 0.8203 0.0301
-8.000 -0.3055 0.01435 0.00785 -0.1097 0.8114 0.0307
-7.750 -0.2819 0.01404 0.00747 -0.1088 0.8026 0.0313
-7.500 -0.2583 0.01374 0.00710 -0.1078 0.7928 0.0320
-7.250 -0.2345 0.01345 0.00673 -0.1069 0.7844 0.0326
-7.000 -0.2106 0.01316 0.00636 -0.1060 0.7760 0.0333
-6.750 -0.1861 0.01292 0.00603 -0.1052 0.7681 0.0341
-6.500 -0.1625 0.01260 0.00567 -0.1042 0.7592 0.0348
-6.250 -0.1387 0.01233 0.00534 -0.1033 0.7510 0.0356
-6.000 -0.1141 0.01209 0.00506 -0.1025 0.7430 0.0364
-5.750 -0.0896 0.01188 0.00478 -0.1016 0.7349 0.0373
-5.500 -0.0648 0.01168 0.00452 -0.1009 0.7264 0.0384
-5.250 -0.0402 0.01152 0.00428 -0.1000 0.7172 0.0394
-5.000 -0.0155 0.01128 0.00403 -0.0992 0.7094 0.0408
-4.750 0.0095 0.01111 0.00382 -0.0984 0.7022 0.0423
-4.500 0.0348 0.01096 0.00362 -0.0977 0.6959 0.0439
-4.250 0.0602 0.01080 0.00343 -0.0970 0.6886 0.0458
-3.750 0.1107 0.01053 0.00312 -0.0956 0.6743 0.0520
-3.500 0.1360 0.01040 0.00298 -0.0949 0.6675 0.0572
-3.250 0.1614 0.01029 0.00286 -0.0943 0.6613 0.0630
-3.000 0.1870 0.01018 0.00276 -0.0936 0.6544 0.0699
-2.750 0.2123 0.01010 0.00265 -0.0929 0.6473 0.0772
-2.500 0.2377 0.01000 0.00256 -0.0923 0.6400 0.0858
-2.250 0.2628 0.00991 0.00248 -0.0915 0.6325 0.0969
-2.000 0.2879 0.00982 0.00241 -0.0908 0.6258 0.1115
-1.750 0.3129 0.00970 0.00236 -0.0901 0.6179 0.1325
-1.500 0.3374 0.00964 0.00233 -0.0893 0.6097 0.1580
-1.250 0.3627 0.00956 0.00231 -0.0886 0.6015 0.1801
-1.000 0.3870 0.00953 0.00229 -0.0878 0.5929 0.2016
-0.750 0.4120 0.00946 0.00227 -0.0871 0.5833 0.2230
-0.500 0.4360 0.00943 0.00225 -0.0861 0.5729 0.2431
-0.250 0.4597 0.00937 0.00224 -0.0852 0.5609 0.2717
0.000 0.4822 0.00925 0.00226 -0.0840 0.5479 0.3304
0.250 0.5038 0.00914 0.00229 -0.0827 0.5335 0.3985
0.500 0.5245 0.00908 0.00234 -0.0812 0.5160 0.4614
0.750 0.5428 0.00900 0.00240 -0.0792 0.4959 0.5422
1.000 0.5590 0.00889 0.00249 -0.0767 0.4776 0.6378
1.250 0.5708 0.00852 0.00261 -0.0731 0.4631 0.8025
1.750 0.7375 0.00911 0.00318 -0.0973 0.4250 0.9883
2.000 0.7775 0.00932 0.00331 -0.1000 0.4161 0.9976
2.250 0.8100 0.00950 0.00342 -0.1011 0.4078 1.0000
2.500 0.8314 0.00965 0.00352 -0.0997 0.4020 1.0000
2.750 0.8535 0.00978 0.00362 -0.0985 0.3959 1.0000
3.000 0.8746 0.00994 0.00374 -0.0971 0.3895 1.0000
3.250 0.8959 0.01010 0.00386 -0.0958 0.3836 1.0000
3.500 0.9176 0.01025 0.00398 -0.0945 0.3767 1.0000
3.750 0.9380 0.01043 0.00412 -0.0930 0.3704 1.0000
4.000 0.9597 0.01058 0.00425 -0.0917 0.3651 1.0000
4.250 0.9809 0.01074 0.00439 -0.0903 0.3588 1.0000
4.500 1.0007 0.01094 0.00456 -0.0887 0.3525 1.0000
4.750 1.0220 0.01110 0.00471 -0.0874 0.3466 1.0000
5.000 1.0421 0.01129 0.00488 -0.0859 0.3397 1.0000
5.250 1.0614 0.01150 0.00506 -0.0842 0.3329 1.0000
5.500 1.0812 0.01169 0.00524 -0.0826 0.3252 1.0000
5.750 1.0988 0.01194 0.00545 -0.0806 0.3176 1.0000
6.000 1.1160 0.01214 0.00564 -0.0786 0.3089 1.0000
6.250 1.1312 0.01239 0.00586 -0.0761 0.3014 1.0000
6.500 1.1470 0.01265 0.00609 -0.0739 0.2910 1.0000
6.750 1.1617 0.01296 0.00635 -0.0714 0.2796 1.0000
7.000 1.1758 0.01333 0.00666 -0.0690 0.2675 1.0000
7.250 1.1908 0.01369 0.00698 -0.0668 0.2570 1.0000
7.500 1.2071 0.01403 0.00730 -0.0648 0.2490 1.0000
7.750 1.2215 0.01447 0.00768 -0.0626 0.2395 1.0000
8.000 1.2379 0.01484 0.00805 -0.0608 0.2311 1.0000
8.250 1.2527 0.01530 0.00848 -0.0588 0.2240 1.0000
8.500 1.2697 0.01569 0.00888 -0.0572 0.2180 1.0000
8.750 1.2852 0.01615 0.00934 -0.0554 0.2119 1.0000
9.000 1.3006 0.01664 0.00982 -0.0537 0.2063 1.0000
9.250 1.3169 0.01710 0.01030 -0.0521 0.2007 1.0000
9.500 1.3304 0.01772 0.01089 -0.0503 0.1943 1.0000
9.750 1.3467 0.01822 0.01143 -0.0489 0.1899 1.0000
10.000 1.3617 0.01880 0.01202 -0.0473 0.1842 1.0000
10.250 1.3746 0.01951 0.01272 -0.0456 0.1789 1.0000
10.500 1.3904 0.02008 0.01334 -0.0443 0.1745 1.0000
10.750 1.4035 0.02083 0.01410 -0.0428 0.1680 1.0000
11.000 1.4164 0.02163 0.01491 -0.0413 0.1627 1.0000
11.250 1.4299 0.02240 0.01570 -0.0400 0.1568 1.0000
11.500 1.4404 0.02339 0.01669 -0.0384 0.1499 1.0000
11.750 1.4522 0.02433 0.01765 -0.0370 0.1418 1.0000
12.000 1.4593 0.02561 0.01889 -0.0354 0.1287 1.0000
12.250 1.4602 0.02739 0.02056 -0.0334 0.1077 1.0000
12.500 1.4479 0.03025 0.02322 -0.0306 0.0787 1.0000
12.750 1.4474 0.03233 0.02527 -0.0290 0.0692 1.0000
13.250 1.4535 0.03613 0.02914 -0.0265 0.0603 1.0000
13.500 1.4570 0.03807 0.03114 -0.0255 0.0578 1.0000
13.750 1.4591 0.04023 0.03334 -0.0246 0.0556 1.0000
14.000 1.4637 0.04220 0.03539 -0.0239 0.0542 1.0000
14.250 1.4675 0.04429 0.03755 -0.0232 0.0528 1.0000
14.500 1.4697 0.04660 0.03994 -0.0227 0.0515 1.0000
14.750 1.4702 0.04917 0.04257 -0.0222 0.0501 1.0000
15.000 1.4690 0.05198 0.04545 -0.0218 0.0491 1.0000
15.250 1.4662 0.05503 0.04858 -0.0216 0.0480 1.0000
15.500 1.4669 0.05777 0.05142 -0.0215 0.0474 1.0000
15.750 1.4666 0.06068 0.05443 -0.0215 0.0467 1.0000
16.000 1.4654 0.06376 0.05759 -0.0216 0.0457 1.0000
16.250 1.4627 0.06707 0.06100 -0.0218 0.0449 1.0000
16.500 1.4583 0.07068 0.06469 -0.0222 0.0440 1.0000
16.750 1.4526 0.07453 0.06862 -0.0227 0.0431 1.0000
17.000 1.4458 0.07859 0.07277 -0.0234 0.0424 1.0000
17.250 1.4362 0.08309 0.07735 -0.0243 0.0416 1.0000
17.500 1.4304 0.08713 0.08148 -0.0251 0.0411 1.0000
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Polar data table (+)
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