GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 217 (MVA MK.12) AIRFOIL (goe217-il) Reynolds number: 200,000 Max Cl/Cd: 67.01 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe217-il-200000.txt Download as CSV file: xf-goe217-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 217 (MVA MK.12) 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
------ -------- --------- --------- -------- -------- --------
-10.500 0.0035 0.09954 0.09611 -0.0753 0.9095 0.1040
-10.250 0.0041 0.09627 0.09278 -0.0773 0.8907 0.1103
-10.000 -0.1141 0.09882 0.09536 -0.0740 0.9438 0.1111
-9.750 -0.0796 0.09633 0.09284 -0.0739 0.9275 0.1125
-9.500 -0.0511 0.09461 0.09105 -0.0740 0.9056 0.1147
-9.250 -0.0564 0.09043 0.08680 -0.0778 0.8823 0.1228
-9.000 -0.0359 0.08936 0.08564 -0.0757 0.8586 0.1247
-8.750 -0.0435 0.08567 0.08189 -0.0788 0.8380 0.1336
-8.500 -0.1775 0.03170 0.02536 -0.1551 0.8304 0.0683
-8.250 -0.1508 0.02969 0.02316 -0.1557 0.8137 0.0660
-8.000 -0.1158 0.02861 0.02139 -0.1583 0.7975 0.0630
-7.750 -0.0897 0.02712 0.01982 -0.1578 0.7829 0.0624
-7.500 -0.0624 0.02592 0.01852 -0.1577 0.7669 0.0619
-7.250 -0.0338 0.02496 0.01740 -0.1579 0.7522 0.0618
-7.000 -0.0050 0.02415 0.01638 -0.1580 0.7389 0.0620
-6.750 0.0235 0.02338 0.01551 -0.1580 0.7242 0.0621
-6.500 0.0516 0.02269 0.01471 -0.1577 0.7115 0.0621
-6.250 0.0794 0.02206 0.01400 -0.1574 0.6984 0.0619
-6.000 0.1072 0.02152 0.01341 -0.1570 0.6863 0.0619
-5.750 0.1350 0.02105 0.01288 -0.1566 0.6748 0.0620
-5.500 0.1633 0.02065 0.01245 -0.1563 0.6641 0.0623
-5.250 0.1920 0.02028 0.01204 -0.1562 0.6538 0.0626
-5.000 0.2214 0.02000 0.01170 -0.1562 0.6448 0.0630
-4.750 0.2506 0.01960 0.01138 -0.1563 0.6353 0.0636
-4.500 0.2823 0.01921 0.01098 -0.1573 0.6273 0.0646
-4.250 0.3165 0.01877 0.01055 -0.1590 0.6187 0.0659
-4.000 0.3511 0.01835 0.01006 -0.1608 0.6105 0.0681
-3.750 0.3859 0.01806 0.00956 -0.1625 0.6034 0.0703
-3.500 0.4208 0.01763 0.00909 -0.1643 0.5960 0.0730
-3.250 0.4541 0.01739 0.00875 -0.1655 0.5893 0.0763
-3.000 0.4880 0.01714 0.00839 -0.1668 0.5835 0.0830
-2.750 0.5273 0.01620 0.00798 -0.1703 0.5777 0.2245
-2.500 0.5601 0.01601 0.00798 -0.1714 0.5718 0.2809
-2.250 0.5914 0.01604 0.00810 -0.1719 0.5665 0.3259
-2.000 0.6216 0.01628 0.00833 -0.1721 0.5617 0.3556
-1.750 0.6512 0.01660 0.00864 -0.1721 0.5569 0.3762
-1.500 0.6803 0.01686 0.00894 -0.1720 0.5519 0.3919
-1.250 0.7099 0.01713 0.00917 -0.1720 0.5472 0.4066
-1.000 0.7382 0.01753 0.00958 -0.1716 0.5432 0.4190
-0.750 0.7671 0.01795 0.00994 -0.1713 0.5395 0.4305
-0.500 0.7952 0.01847 0.01047 -0.1709 0.5359 0.4409
-0.250 0.8230 0.01884 0.01091 -0.1705 0.5321 0.4513
0.000 0.8494 0.01933 0.01150 -0.1697 0.5281 0.4599
0.250 0.8793 0.01957 0.01166 -0.1699 0.5242 0.4705
0.500 0.9067 0.01990 0.01201 -0.1693 0.5207 0.4750
0.750 0.9350 0.02031 0.01238 -0.1690 0.5177 0.4811
1.000 0.9660 0.02066 0.01263 -0.1697 0.5146 0.4910
1.250 0.9924 0.02091 0.01302 -0.1692 0.5114 0.4951
1.500 1.0190 0.02120 0.01338 -0.1686 0.5073 0.4994
1.750 1.0470 0.02136 0.01353 -0.1684 0.5025 0.5052
2.000 1.0788 0.02142 0.01340 -0.1691 0.4978 0.5140
2.250 1.1053 0.02174 0.01373 -0.1686 0.4930 0.5176
2.500 1.1304 0.02190 0.01402 -0.1678 0.4878 0.5218
2.750 1.1574 0.02204 0.01417 -0.1674 0.4826 0.5274
3.000 1.1885 0.02212 0.01412 -0.1680 0.4783 0.5363
3.250 1.2153 0.02243 0.01442 -0.1675 0.4747 0.5402
3.500 1.2401 0.02279 0.01488 -0.1667 0.4709 0.5450
3.750 1.2661 0.02301 0.01518 -0.1663 0.4667 0.5514
4.000 1.2958 0.02311 0.01525 -0.1668 0.4624 0.5584
4.250 1.3225 0.02321 0.01537 -0.1664 0.4584 0.5617
4.500 1.3504 0.02341 0.01552 -0.1662 0.4547 0.5656
4.750 1.3765 0.02369 0.01585 -0.1659 0.4505 0.5701
5.000 1.4027 0.02383 0.01607 -0.1658 0.4459 0.5755
5.250 1.4301 0.02391 0.01615 -0.1658 0.4411 0.5805
5.500 1.4568 0.02397 0.01621 -0.1654 0.4368 0.5840
5.750 1.4848 0.02420 0.01636 -0.1654 0.4324 0.5878
6.000 1.5072 0.02435 0.01667 -0.1645 0.4271 0.5920
6.250 1.5330 0.02444 0.01678 -0.1643 0.4216 0.5975
6.500 1.5595 0.02447 0.01677 -0.1640 0.4167 0.6017
6.750 1.5847 0.02465 0.01695 -0.1635 0.4116 0.6053
7.000 1.6049 0.02481 0.01726 -0.1623 0.4052 0.6090
7.250 1.6286 0.02485 0.01731 -0.1616 0.3989 0.6135
7.500 1.6544 0.02499 0.01735 -0.1613 0.3927 0.6187
7.750 1.6711 0.02515 0.01770 -0.1595 0.3850 0.6221
8.000 1.6913 0.02524 0.01778 -0.1582 0.3778 0.6261
8.250 1.7081 0.02551 0.01814 -0.1564 0.3695 0.6303
8.500 1.7241 0.02573 0.01837 -0.1546 0.3603 0.6347
8.750 1.7368 0.02610 0.01879 -0.1523 0.3499 0.6385
9.000 1.7454 0.02648 0.01912 -0.1492 0.3397 0.6417
9.250 1.7457 0.02710 0.01986 -0.1450 0.3273 0.6453
9.500 1.7497 0.02799 0.02073 -0.1418 0.3144 0.6497
9.750 1.7522 0.02916 0.02184 -0.1388 0.3016 0.6541
10.000 1.7527 0.03058 0.02320 -0.1358 0.2894 0.6573
10.250 1.7540 0.03216 0.02479 -0.1334 0.2780 0.6605
10.500 1.7540 0.03399 0.02658 -0.1310 0.2688 0.6640
10.750 1.7551 0.03592 0.02849 -0.1290 0.2605 0.6679
11.000 1.7566 0.03795 0.03046 -0.1273 0.2538 0.6720
11.250 1.7597 0.03989 0.03246 -0.1258 0.2474 0.6756
11.500 1.7620 0.04193 0.03444 -0.1242 0.2421 0.6798
11.750 1.7666 0.04389 0.03644 -0.1230 0.2372 0.6846
12.000 1.7704 0.04601 0.03862 -0.1219 0.2325 0.6892
12.250 1.7753 0.04795 0.04054 -0.1208 0.2283 0.6930
12.500 1.7848 0.04945 0.04196 -0.1197 0.2243 0.6977
12.750 1.7871 0.05180 0.04445 -0.1189 0.2208 0.7024
13.000 1.7909 0.05401 0.04674 -0.1181 0.2173 0.7069
13.250 1.7964 0.05598 0.04874 -0.1173 0.2140 0.7119
13.500 1.8083 0.05727 0.04995 -0.1163 0.2108 0.7184
13.750 1.8166 0.05900 0.05173 -0.1155 0.2081 0.7244
14.000 1.8173 0.06160 0.05449 -0.1149 0.2054 0.7301
14.250 1.8199 0.06404 0.05702 -0.1144 0.2026 0.7363
14.500 1.8247 0.06620 0.05924 -0.1139 0.1998 0.7424
14.750 1.8340 0.06780 0.06084 -0.1132 0.1971 0.7502
15.000 1.8536 0.06818 0.06115 -0.1122 0.1943 0.7600
15.250 1.8475 0.07172 0.06492 -0.1121 0.1923 0.7680
15.500 1.8450 0.07491 0.06831 -0.1120 0.1899 0.7793
16.000 1.8467 0.07980 0.07350 -0.1113 0.1850 1.0000
16.250 1.8560 0.08149 0.07516 -0.1110 0.1826 1.0000
16.500 1.8749 0.08192 0.07550 -0.1101 0.1800 1.0000
16.750 1.8626 0.08656 0.08037 -0.1107 0.1782 1.0000
17.000 1.8544 0.09072 0.08470 -0.1113 0.1760 1.0000
17.250 1.8508 0.09429 0.08840 -0.1119 0.1736 1.0000
17.500 1.8533 0.09699 0.09115 -0.1121 0.1713 1.0000
17.750 1.8627 0.09863 0.09277 -0.1120 0.1691 1.0000
18.000 1.8842 0.09844 0.09246 -0.1110 0.1665 1.0000
18.250 1.8605 0.10499 0.09930 -0.1130 0.1646 1.0000
18.500 1.8436 0.11068 0.10521 -0.1148 0.1621 1.0000
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Polar data table (+)
Polar graphs
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