GOE 701 AIRFOIL (goe701-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 701 AIRFOIL (goe701-il) Reynolds number: 200,000 Max Cl/Cd: 78.87 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe701-il-200000.txt Download as CSV file: xf-goe701-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 701 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2654 0.09145 0.08797 -0.0547 0.9810 0.0923
-8.250 -0.2899 0.08519 0.08171 -0.0728 0.9638 0.0980
-8.000 -0.2791 0.07802 0.07451 -0.0794 0.9577 0.0990
-7.750 -0.2491 0.07682 0.07332 -0.0753 0.9572 0.1004
-7.500 -0.2198 0.07424 0.07071 -0.0772 0.9553 0.1025
-7.250 -0.2738 0.05189 0.04782 -0.0980 0.9312 0.0871
-7.000 -0.2559 0.04603 0.04171 -0.1015 0.9265 0.0850
-6.750 -0.2546 0.03957 0.03484 -0.1021 0.9176 0.0842
-6.500 -0.2482 0.03241 0.02682 -0.1028 0.9110 0.0853
-6.250 -0.2212 0.02859 0.02242 -0.1045 0.9086 0.0872
-6.000 -0.2067 0.02762 0.02138 -0.1023 0.8997 0.0885
-5.750 -0.1720 0.02667 0.02039 -0.1039 0.8965 0.0907
-5.500 -0.1354 0.02537 0.01887 -0.1058 0.8943 0.0938
-5.250 -0.0997 0.02369 0.01676 -0.1075 0.8923 0.0970
-5.000 -0.0859 0.02274 0.01553 -0.1048 0.8829 0.0989
-4.750 -0.0513 0.02165 0.01445 -0.1062 0.8797 0.1020
-4.500 -0.0136 0.02096 0.01369 -0.1080 0.8773 0.1062
-4.250 0.0107 0.02039 0.01291 -0.1071 0.8708 0.1100
-4.000 0.0390 0.01941 0.01179 -0.1071 0.8653 0.1139
-3.750 0.0753 0.01884 0.01124 -0.1086 0.8621 0.1193
-3.500 0.1134 0.01830 0.01050 -0.1102 0.8594 0.1260
-3.250 0.1306 0.01780 0.01006 -0.1081 0.8501 0.1309
-3.000 0.1651 0.01738 0.00957 -0.1091 0.8460 0.1386
-2.750 0.1993 0.01683 0.00900 -0.1101 0.8420 0.1463
-2.500 0.2204 0.01675 0.00890 -0.1086 0.8334 0.1530
-2.250 0.2543 0.01628 0.00836 -0.1095 0.8288 0.1605
-2.000 0.2807 0.01613 0.00824 -0.1090 0.8221 0.1674
-1.750 0.3082 0.01597 0.00798 -0.1087 0.8152 0.1744
-1.500 0.3427 0.01554 0.00760 -0.1097 0.8107 0.1821
-1.250 0.3640 0.01554 0.00755 -0.1083 0.8020 0.1891
-1.000 0.3947 0.01518 0.00724 -0.1086 0.7961 0.1975
-0.750 0.4213 0.01510 0.00712 -0.1081 0.7891 0.2063
-0.500 0.4472 0.01481 0.00690 -0.1075 0.7815 0.2144
-0.250 0.4790 0.01454 0.00660 -0.1080 0.7756 0.2260
0.000 0.5002 0.01436 0.00651 -0.1064 0.7656 0.2383
0.250 0.5294 0.01402 0.00621 -0.1064 0.7578 0.2565
0.500 0.5519 0.01372 0.00603 -0.1050 0.7472 0.2799
0.750 0.5751 0.01340 0.00589 -0.1038 0.7371 0.3192
1.000 0.5968 0.01271 0.00572 -0.1023 0.7279 0.4629
1.250 0.7366 0.01162 0.00571 -0.1250 0.7171 1.0000
1.500 0.7631 0.01166 0.00561 -0.1245 0.7095 1.0000
1.750 0.7818 0.01177 0.00569 -0.1225 0.6991 1.0000
2.000 0.8057 0.01184 0.00566 -0.1215 0.6903 1.0000
2.250 0.8267 0.01191 0.00568 -0.1199 0.6799 1.0000
2.500 0.8478 0.01201 0.00573 -0.1183 0.6696 1.0000
2.750 0.8721 0.01207 0.00569 -0.1173 0.6602 1.0000
3.000 0.8906 0.01219 0.00581 -0.1153 0.6488 1.0000
3.250 0.9122 0.01229 0.00586 -0.1138 0.6384 1.0000
3.500 0.9345 0.01238 0.00588 -0.1125 0.6274 1.0000
3.750 0.9527 0.01250 0.00598 -0.1104 0.6145 1.0000
4.000 0.9721 0.01263 0.00608 -0.1085 0.6017 1.0000
4.250 0.9920 0.01277 0.00616 -0.1067 0.5888 1.0000
4.500 1.0117 0.01292 0.00625 -0.1049 0.5756 1.0000
4.750 1.0304 0.01309 0.00635 -0.1029 0.5612 1.0000
5.000 1.0474 0.01328 0.00650 -0.1005 0.5453 1.0000
5.250 1.0638 0.01350 0.00666 -0.0981 0.5285 1.0000
5.500 1.0787 0.01374 0.00684 -0.0954 0.5102 1.0000
5.750 1.0927 0.01401 0.00706 -0.0926 0.4910 1.0000
6.000 1.1051 0.01432 0.00729 -0.0895 0.4699 1.0000
6.250 1.1158 0.01469 0.00754 -0.0861 0.4477 1.0000
6.500 1.1252 0.01510 0.00785 -0.0825 0.4243 1.0000
6.750 1.1323 0.01557 0.00820 -0.0785 0.4017 1.0000
7.000 1.1387 0.01609 0.00857 -0.0745 0.3818 1.0000
7.250 1.1465 0.01663 0.00900 -0.0708 0.3627 1.0000
7.500 1.1561 0.01720 0.00947 -0.0676 0.3464 1.0000
8.000 1.1795 0.01835 0.01048 -0.0622 0.3198 1.0000
8.250 1.1933 0.01893 0.01103 -0.0600 0.3090 1.0000
8.500 1.2073 0.01958 0.01157 -0.0579 0.2998 1.0000
8.750 1.2214 0.02011 0.01214 -0.0558 0.2903 1.0000
9.000 1.2357 0.02076 0.01273 -0.0538 0.2818 1.0000
9.250 1.2494 0.02134 0.01334 -0.0518 0.2735 1.0000
9.500 1.2638 0.02201 0.01397 -0.0500 0.2658 1.0000
9.750 1.2775 0.02260 0.01463 -0.0481 0.2585 1.0000
10.000 1.2930 0.02333 0.01528 -0.0465 0.2517 1.0000
10.250 1.3051 0.02395 0.01602 -0.0445 0.2448 1.0000
10.500 1.3190 0.02469 0.01671 -0.0428 0.2385 1.0000
10.750 1.3313 0.02541 0.01752 -0.0409 0.2319 1.0000
11.000 1.3415 0.02617 0.01832 -0.0389 0.2251 1.0000
11.250 1.3536 0.02700 0.01917 -0.0372 0.2189 1.0000
11.500 1.3642 0.02781 0.02009 -0.0353 0.2129 1.0000
11.750 1.3744 0.02872 0.02098 -0.0336 0.2069 1.0000
12.000 1.3840 0.02964 0.02203 -0.0318 0.2010 1.0000
12.250 1.3928 0.03061 0.02309 -0.0301 0.1951 1.0000
12.500 1.4003 0.03173 0.02422 -0.0284 0.1889 1.0000
12.750 1.4079 0.03283 0.02549 -0.0268 0.1823 1.0000
13.000 1.4135 0.03413 0.02680 -0.0252 0.1762 1.0000
13.250 1.4215 0.03534 0.02818 -0.0238 0.1692 1.0000
13.500 1.4258 0.03685 0.02973 -0.0224 0.1623 1.0000
13.750 1.4317 0.03835 0.03136 -0.0213 0.1525 1.0000
14.000 1.4349 0.04015 0.03321 -0.0201 0.1412 1.0000
14.250 1.4350 0.04232 0.03539 -0.0190 0.1265 1.0000
14.500 1.4315 0.04496 0.03798 -0.0179 0.1104 1.0000
14.750 1.4232 0.04819 0.04113 -0.0169 0.0910 1.0000
15.000 1.4116 0.05191 0.04476 -0.0160 0.0737 1.0000
15.250 1.4003 0.05579 0.04858 -0.0154 0.0595 1.0000
15.500 1.3895 0.05977 0.05256 -0.0151 0.0527 1.0000
15.750 1.3792 0.06388 0.05670 -0.0151 0.0491 1.0000
16.000 1.3689 0.06816 0.06107 -0.0153 0.0465 1.0000
16.250 1.3582 0.07264 0.06565 -0.0159 0.0449 1.0000
16.500 1.3452 0.07757 0.07068 -0.0167 0.0436 1.0000
16.750 1.3310 0.08286 0.07607 -0.0178 0.0426 1.0000
17.000 1.3210 0.08765 0.08099 -0.0189 0.0417 1.0000
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