E197 (13.49%) (e197-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E197 (13.49%) (e197-il) Reynolds number: 200,000 Max Cl/Cd: 75.86 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e197-il-200000-n5.txt Download as CSV file: xf-e197-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E197 (13.49%)
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4529 0.10190 0.09826 -0.0403 1.0000 0.0179
-11.750 -0.6114 0.06024 0.05627 -0.0663 1.0000 0.0161
-11.500 -0.6404 0.05287 0.04864 -0.0721 1.0000 0.0159
-11.250 -0.6591 0.04828 0.04387 -0.0747 1.0000 0.0158
-11.000 -0.6761 0.04487 0.04031 -0.0751 1.0000 0.0159
-10.750 -0.6921 0.04246 0.03776 -0.0731 1.0000 0.0160
-10.500 -0.7066 0.04054 0.03573 -0.0695 1.0000 0.0161
-10.250 -0.7149 0.03857 0.03361 -0.0664 1.0000 0.0162
-10.000 -0.7103 0.03656 0.03144 -0.0653 0.9956 0.0165
-9.750 -0.6877 0.03427 0.02891 -0.0675 0.9841 0.0170
-9.500 -0.6637 0.03234 0.02675 -0.0693 0.9715 0.0178
-9.250 -0.6402 0.03020 0.02430 -0.0705 0.9567 0.0185
-9.000 -0.6156 0.02814 0.02192 -0.0715 0.9407 0.0190
-8.750 -0.5894 0.02625 0.01971 -0.0724 0.9243 0.0195
-8.500 -0.5623 0.02468 0.01787 -0.0732 0.9075 0.0199
-8.250 -0.5359 0.02335 0.01630 -0.0735 0.8899 0.0204
-8.000 -0.5112 0.02220 0.01494 -0.0734 0.8723 0.0208
-7.750 -0.4900 0.02087 0.01348 -0.0728 0.8556 0.0215
-7.500 -0.4682 0.02003 0.01251 -0.0721 0.8400 0.0225
-7.250 -0.4460 0.01934 0.01170 -0.0714 0.8257 0.0236
-7.000 -0.4238 0.01867 0.01089 -0.0706 0.8123 0.0247
-6.750 -0.4017 0.01799 0.01006 -0.0697 0.8000 0.0256
-6.500 -0.3792 0.01737 0.00928 -0.0689 0.7890 0.0265
-6.250 -0.3565 0.01678 0.00853 -0.0681 0.7792 0.0277
-6.000 -0.3336 0.01619 0.00784 -0.0674 0.7691 0.0296
-5.750 -0.3096 0.01573 0.00727 -0.0668 0.7603 0.0323
-5.500 -0.2853 0.01530 0.00673 -0.0663 0.7520 0.0368
-5.250 -0.2613 0.01480 0.00623 -0.0658 0.7441 0.0485
-5.000 -0.2371 0.01433 0.00577 -0.0652 0.7368 0.0698
-4.750 -0.2125 0.01391 0.00540 -0.0649 0.7296 0.0960
-4.500 -0.1877 0.01353 0.00508 -0.0645 0.7229 0.1253
-4.250 -0.1629 0.01314 0.00479 -0.0642 0.7166 0.1635
-4.000 -0.1387 0.01268 0.00452 -0.0638 0.7102 0.2190
-3.750 -0.1147 0.01225 0.00429 -0.0634 0.7048 0.2838
-3.500 -0.0902 0.01190 0.00417 -0.0630 0.6987 0.3471
-3.250 -0.0646 0.01172 0.00406 -0.0626 0.6933 0.3939
-3.000 -0.0384 0.01160 0.00397 -0.0623 0.6881 0.4333
-2.750 -0.0120 0.01150 0.00390 -0.0620 0.6825 0.4649
-2.500 0.0147 0.01145 0.00381 -0.0617 0.6778 0.4895
-2.250 0.0415 0.01139 0.00375 -0.0615 0.6728 0.5103
-2.000 0.0683 0.01133 0.00368 -0.0613 0.6676 0.5304
-1.750 0.0954 0.01130 0.00362 -0.0610 0.6632 0.5501
-1.500 0.1222 0.01126 0.00358 -0.0608 0.6586 0.5690
-1.250 0.1490 0.01121 0.00356 -0.0606 0.6536 0.5879
-1.000 0.1760 0.01118 0.00353 -0.0604 0.6492 0.6066
-0.500 0.2295 0.01111 0.00352 -0.0598 0.6402 0.6465
-0.250 0.2561 0.01108 0.00353 -0.0595 0.6358 0.6691
0.000 0.2827 0.01105 0.00353 -0.0592 0.6321 0.6926
0.250 0.3090 0.01102 0.00359 -0.0588 0.6272 0.7179
0.500 0.3351 0.01098 0.00364 -0.0583 0.6227 0.7445
0.750 0.3615 0.01096 0.00368 -0.0578 0.6188 0.7729
1.000 0.3879 0.01095 0.00375 -0.0574 0.6146 0.8041
1.250 0.4153 0.01095 0.00385 -0.0571 0.6098 0.8373
1.500 0.4460 0.01097 0.00393 -0.0575 0.6056 0.8720
1.750 0.4815 0.01103 0.00400 -0.0589 0.6017 0.9044
2.000 0.5193 0.01110 0.00412 -0.0610 0.5965 0.9328
2.250 0.5561 0.01118 0.00421 -0.0629 0.5919 0.9564
2.500 0.5940 0.01127 0.00425 -0.0650 0.5880 0.9740
2.750 0.6323 0.01135 0.00438 -0.0675 0.5825 0.9881
3.000 0.6710 0.01144 0.00449 -0.0700 0.5774 1.0000
3.250 0.6948 0.01156 0.00456 -0.0693 0.5734 1.0000
3.500 0.7179 0.01168 0.00474 -0.0685 0.5677 1.0000
3.750 0.7415 0.01179 0.00487 -0.0677 0.5623 1.0000
4.000 0.7655 0.01192 0.00499 -0.0670 0.5570 1.0000
4.250 0.7888 0.01203 0.00515 -0.0662 0.5497 1.0000
4.500 0.8128 0.01214 0.00525 -0.0655 0.5433 1.0000
4.750 0.8362 0.01226 0.00545 -0.0647 0.5349 1.0000
5.000 0.8601 0.01238 0.00557 -0.0640 0.5274 1.0000
5.250 0.8837 0.01250 0.00574 -0.0632 0.5182 1.0000
5.500 0.9073 0.01263 0.00592 -0.0624 0.5086 1.0000
5.750 0.9308 0.01276 0.00609 -0.0616 0.4987 1.0000
6.000 0.9539 0.01291 0.00627 -0.0608 0.4874 1.0000
6.250 0.9766 0.01307 0.00647 -0.0599 0.4743 1.0000
6.500 0.9989 0.01326 0.00668 -0.0589 0.4597 1.0000
6.750 1.0205 0.01348 0.00691 -0.0578 0.4436 1.0000
7.000 1.0415 0.01373 0.00721 -0.0566 0.4239 1.0000
7.250 1.0605 0.01407 0.00750 -0.0552 0.4002 1.0000
7.500 1.0776 0.01450 0.00786 -0.0534 0.3697 1.0000
7.750 1.0917 0.01509 0.00831 -0.0513 0.3328 1.0000
8.000 1.1025 0.01584 0.00888 -0.0487 0.2937 1.0000
8.250 1.1103 0.01673 0.00961 -0.0457 0.2564 1.0000
8.500 1.1162 0.01769 0.01040 -0.0426 0.2210 1.0000
8.750 1.1190 0.01865 0.01122 -0.0390 0.1916 1.0000
9.000 1.1211 0.01968 0.01213 -0.0354 0.1649 1.0000
9.250 1.1216 0.02090 0.01319 -0.0321 0.1372 1.0000
9.500 1.1239 0.02216 0.01434 -0.0292 0.1155 1.0000
9.750 1.1262 0.02352 0.01560 -0.0267 0.0953 1.0000
10.000 1.1289 0.02498 0.01696 -0.0245 0.0785 1.0000
10.250 1.1334 0.02642 0.01837 -0.0227 0.0658 1.0000
10.500 1.1388 0.02789 0.01985 -0.0212 0.0565 1.0000
10.750 1.1435 0.02949 0.02144 -0.0198 0.0465 1.0000
11.000 1.1480 0.03118 0.02313 -0.0185 0.0377 1.0000
11.250 1.1531 0.03289 0.02488 -0.0173 0.0315 1.0000
11.500 1.1565 0.03481 0.02682 -0.0162 0.0261 1.0000
11.750 1.1590 0.03687 0.02890 -0.0152 0.0213 1.0000
12.000 1.1620 0.03895 0.03106 -0.0143 0.0185 1.0000
12.250 1.1650 0.04108 0.03326 -0.0136 0.0167 1.0000
12.500 1.1654 0.04352 0.03575 -0.0129 0.0153 1.0000
12.750 1.1684 0.04577 0.03812 -0.0123 0.0144 1.0000
13.000 1.1708 0.04811 0.04059 -0.0119 0.0131 1.0000
13.250 1.1721 0.05065 0.04321 -0.0116 0.0122 1.0000
13.750 1.1727 0.05618 0.04893 -0.0114 0.0110 1.0000
14.000 1.1735 0.05902 0.05190 -0.0115 0.0108 1.0000
14.250 1.1729 0.06211 0.05512 -0.0117 0.0104 1.0000
14.500 1.1723 0.06528 0.05842 -0.0120 0.0102 1.0000
14.750 1.1719 0.06853 0.06178 -0.0124 0.0099 1.0000
15.000 1.1710 0.07191 0.06528 -0.0130 0.0098 1.0000
15.250 1.1693 0.07547 0.06896 -0.0137 0.0095 1.0000
15.500 1.1673 0.07919 0.07279 -0.0146 0.0092 1.0000
15.750 1.1653 0.08298 0.07670 -0.0156 0.0091 1.0000
16.000 1.1632 0.08687 0.08071 -0.0167 0.0090 1.0000
16.250 1.1602 0.09096 0.08493 -0.0180 0.0088 1.0000
16.500 1.1571 0.09513 0.08922 -0.0193 0.0087 1.0000
16.750 1.1541 0.09938 0.09359 -0.0208 0.0087 1.0000
17.000 1.1501 0.10386 0.09818 -0.0225 0.0085 1.0000
17.250 1.1452 0.10847 0.10290 -0.0242 0.0083 1.0000
17.500 1.1417 0.11301 0.10755 -0.0260 0.0083 1.0000
17.750 1.1374 0.11787 0.11257 -0.0282 0.0082 1.0000
18.000 1.1328 0.12289 0.11775 -0.0306 0.0082 1.0000
18.250 1.1280 0.12801 0.12301 -0.0331 0.0082 1.0000
18.500 1.1202 0.13391 0.12909 -0.0363 0.0081 1.0000
18.750 1.1133 0.13975 0.13509 -0.0395 0.0081 1.0000
19.000 1.1049 0.14609 0.14160 -0.0432 0.0081 1.0000
19.250 1.0965 0.15259 0.14825 -0.0470 0.0081 1.0000
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Polar data table (+)
Polar graphs
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