GOE 14K AIRFOIL (goe14k-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 14K AIRFOIL (goe14k-il) Reynolds number: 200,000 Max Cl/Cd: 59.78 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe14k-il-200000-n5.txt Download as CSV file: xf-goe14k-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 14K 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7107 0.04402 0.03926 -0.0919 0.9577 0.0134
-10.500 -0.7223 0.04252 0.03762 -0.0866 0.9518 0.0136
-10.250 -0.7187 0.04187 0.03689 -0.0835 0.9474 0.0142
-10.000 -0.7199 0.03918 0.03386 -0.0804 0.9443 0.0144
-9.750 -0.7288 0.03751 0.03194 -0.0746 0.9375 0.0148
-9.500 -0.7259 0.03532 0.02940 -0.0711 0.9336 0.0150
-9.250 -0.7167 0.03317 0.02684 -0.0687 0.9313 0.0159
-9.000 -0.7075 0.03143 0.02477 -0.0658 0.9286 0.0162
-8.750 -0.7077 0.03031 0.02340 -0.0606 0.9229 0.0165
-8.500 -0.6959 0.02896 0.02190 -0.0582 0.9202 0.0172
-8.250 -0.6769 0.02826 0.02113 -0.0570 0.9183 0.0183
-8.000 -0.6557 0.02734 0.02003 -0.0562 0.9169 0.0197
-7.750 -0.6331 0.02618 0.01860 -0.0555 0.9158 0.0209
-7.500 -0.6334 0.02559 0.01786 -0.0499 0.9095 0.0216
-7.250 -0.6181 0.02475 0.01694 -0.0478 0.9069 0.0233
-7.000 -0.5968 0.02429 0.01639 -0.0468 0.9051 0.0251
-6.750 -0.5738 0.02363 0.01560 -0.0460 0.9037 0.0271
-6.500 -0.5504 0.02283 0.01465 -0.0453 0.9026 0.0301
-6.250 -0.5251 0.02235 0.01414 -0.0451 0.9016 0.0340
-6.000 -0.5182 0.02226 0.01396 -0.0409 0.8970 0.0370
-5.750 -0.5015 0.02200 0.01356 -0.0387 0.8936 0.0412
-5.500 -0.4806 0.02164 0.01316 -0.0375 0.8916 0.0458
-5.250 -0.4566 0.02140 0.01282 -0.0370 0.8901 0.0518
-5.000 -0.4313 0.02108 0.01237 -0.0366 0.8889 0.0567
-4.750 -0.4062 0.02071 0.01197 -0.0363 0.8878 0.0619
-4.500 -0.3794 0.02041 0.01157 -0.0364 0.8870 0.0664
-4.250 -0.3725 0.02033 0.01146 -0.0322 0.8824 0.0696
-4.000 -0.3578 0.02017 0.01129 -0.0297 0.8791 0.0735
-3.750 -0.3363 0.02001 0.01104 -0.0286 0.8771 0.0781
-3.500 -0.3130 0.01973 0.01074 -0.0278 0.8755 0.0829
-3.250 -0.2871 0.01946 0.01044 -0.0276 0.8742 0.0885
-3.000 -0.2593 0.01920 0.01014 -0.0278 0.8731 0.0947
-2.750 -0.2312 0.01891 0.00990 -0.0280 0.8722 0.1076
-2.500 -0.2032 0.01855 0.00971 -0.0284 0.8715 0.1473
-2.250 -0.2074 0.01882 0.01007 -0.0220 0.8644 0.1748
-2.000 -0.1844 0.01860 0.01002 -0.0213 0.8623 0.2224
-1.750 -0.1592 0.01832 0.00996 -0.0211 0.8606 0.2814
-1.250 0.1109 0.01694 0.01095 -0.0700 0.8754 0.8727
-1.000 0.1558 0.01743 0.01140 -0.0735 0.8750 0.9222
-0.750 0.1830 0.01769 0.01160 -0.0733 0.8737 0.9469
-0.500 0.2229 0.01816 0.01202 -0.0759 0.8732 0.9678
-0.250 0.2813 0.01852 0.01234 -0.0828 0.8734 0.9815
0.000 0.3355 0.01856 0.01236 -0.0888 0.8734 0.9895
0.250 0.3863 0.01851 0.01229 -0.0942 0.8732 0.9956
0.500 0.4351 0.01832 0.01211 -0.0992 0.8730 1.0000
0.750 0.4680 0.01804 0.01182 -0.1004 0.8719 1.0000
1.250 0.4952 0.01828 0.01208 -0.0950 0.8604 1.0000
1.500 0.5278 0.01797 0.01179 -0.0960 0.8588 1.0000
1.750 0.5618 0.01766 0.01151 -0.0974 0.8574 1.0000
2.000 0.5961 0.01736 0.01124 -0.0988 0.8560 1.0000
2.250 0.5919 0.01786 0.01177 -0.0924 0.8459 1.0000
2.500 0.6329 0.01721 0.01118 -0.0949 0.8435 1.0000
2.750 0.6540 0.01687 0.01088 -0.0932 0.8344 1.0000
3.000 0.7141 0.01538 0.00944 -0.0990 0.8245 1.0000
3.250 0.7425 0.01484 0.00893 -0.0986 0.8100 1.0000
3.500 0.7559 0.01471 0.00883 -0.0953 0.7938 1.0000
3.750 0.7644 0.01474 0.00889 -0.0910 0.7764 1.0000
4.000 0.7740 0.01481 0.00902 -0.0870 0.7581 1.0000
4.250 0.7972 0.01449 0.00865 -0.0856 0.7122 1.0000
4.500 0.8500 0.01422 0.00750 -0.0901 0.5501 1.0000
4.750 0.8363 0.01517 0.00796 -0.0814 0.4613 1.0000
5.000 0.8280 0.01606 0.00851 -0.0742 0.4016 1.0000
5.250 0.8290 0.01677 0.00902 -0.0689 0.3535 1.0000
5.500 0.8318 0.01748 0.00951 -0.0642 0.3003 1.0000
5.750 0.8327 0.01838 0.01009 -0.0592 0.2358 1.0000
6.000 0.8382 0.01920 0.01065 -0.0553 0.1863 1.0000
6.250 0.8465 0.01995 0.01119 -0.0519 0.1477 1.0000
6.750 0.8699 0.02119 0.01223 -0.0464 0.1018 1.0000
7.000 0.8828 0.02177 0.01277 -0.0439 0.0882 1.0000
7.250 0.8961 0.02235 0.01331 -0.0415 0.0779 1.0000
7.500 0.9100 0.02290 0.01388 -0.0392 0.0695 1.0000
7.750 0.9241 0.02346 0.01446 -0.0370 0.0606 1.0000
8.000 0.9385 0.02403 0.01508 -0.0349 0.0513 1.0000
8.250 0.9521 0.02467 0.01572 -0.0327 0.0434 1.0000
8.500 0.9658 0.02533 0.01640 -0.0304 0.0355 1.0000
8.750 0.9781 0.02613 0.01722 -0.0280 0.0303 1.0000
9.000 0.9910 0.02688 0.01805 -0.0257 0.0268 1.0000
9.250 1.0027 0.02773 0.01893 -0.0233 0.0250 1.0000
9.500 1.0116 0.02886 0.02012 -0.0205 0.0228 1.0000
9.750 1.0245 0.02970 0.02108 -0.0183 0.0210 1.0000
10.000 1.0365 0.03059 0.02205 -0.0161 0.0196 1.0000
10.250 1.0473 0.03162 0.02317 -0.0138 0.0189 1.0000
10.500 1.0564 0.03283 0.02444 -0.0113 0.0179 1.0000
10.750 1.0676 0.03389 0.02565 -0.0092 0.0166 1.0000
11.000 1.0780 0.03510 0.02699 -0.0069 0.0161 1.0000
11.250 1.0883 0.03630 0.02831 -0.0047 0.0153 1.0000
11.500 1.0977 0.03756 0.02968 -0.0025 0.0148 1.0000
11.750 1.1053 0.03889 0.03108 -0.0003 0.0142 1.0000
12.000 1.1125 0.04044 0.03272 0.0020 0.0139 1.0000
12.250 1.1190 0.04218 0.03465 0.0044 0.0133 1.0000
12.500 1.1252 0.04394 0.03663 0.0067 0.0129 1.0000
12.750 1.1290 0.04575 0.03865 0.0092 0.0123 1.0000
13.000 1.1310 0.04786 0.04097 0.0116 0.0120 1.0000
13.250 1.1323 0.04956 0.04281 0.0139 0.0117 1.0000
13.500 1.1301 0.05233 0.04586 0.0165 0.0119 1.0000
13.750 1.1270 0.05454 0.04825 0.0188 0.0115 1.0000
14.000 1.1224 0.05703 0.05092 0.0209 0.0112 1.0000
14.250 1.1201 0.05908 0.05299 0.0225 0.0109 1.0000
14.500 1.1100 0.06257 0.05672 0.0245 0.0109 1.0000
14.750 1.0992 0.06601 0.06031 0.0260 0.0106 1.0000
15.000 1.0846 0.07017 0.06474 0.0270 0.0105 1.0000
15.250 1.0716 0.07439 0.06913 0.0275 0.0106 1.0000
15.500 1.0541 0.07953 0.07449 0.0274 0.0106 1.0000
15.750 1.0298 0.08617 0.08142 0.0259 0.0105 1.0000
16.000 1.0065 0.09336 0.08887 0.0233 0.0105 1.0000
16.250 0.9887 0.10013 0.09578 0.0204 0.0106 1.0000
16.500 0.9696 0.10779 0.10359 0.0165 0.0106 1.0000
16.750 0.9436 0.11785 0.11384 0.0108 0.0106 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 14K AIRFOIL (goe14k-il)