BELL/WORTMANN FX 69-H-098 AIRFOIL (fx69h098-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BELL/WORTMANN FX 69-H-098 AIRFOIL (fx69h098-il) Reynolds number: 100,000 Max Cl/Cd: 43.68 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx69h098-il-100000.txt Download as CSV file: xf-fx69h098-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BELL/WORTMANN FX 69-H-098 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5197 0.11077 0.10581 -0.0058 1.0000 0.0970
-9.500 -0.5404 0.10708 0.10223 -0.0138 1.0000 0.0995
-9.250 -0.5643 0.10239 0.09764 -0.0230 1.0000 0.0999
-9.000 -0.4170 0.08970 0.08514 -0.0193 1.0000 0.1169
-8.750 -0.4078 0.08657 0.08202 -0.0183 1.0000 0.1236
-8.500 -0.4292 0.08216 0.07768 -0.0224 1.0000 0.1274
-8.250 -0.4580 0.07713 0.07274 -0.0278 1.0000 0.1281
-8.000 -0.4221 0.07427 0.06986 -0.0212 1.0000 0.1372
-7.750 -0.4460 0.06963 0.06530 -0.0249 1.0000 0.1408
-7.500 -0.5631 0.07365 0.06883 -0.0282 1.0000 0.1295
-7.250 -0.4592 0.06151 0.05726 -0.0243 1.0000 0.1496
-7.000 -0.4885 0.05724 0.05290 -0.0261 1.0000 0.1568
-6.500 -0.5318 0.06089 0.05615 -0.0228 1.0000 0.1637
-6.250 -0.5309 0.05777 0.05295 -0.0219 1.0000 0.1761
-6.000 -0.5262 0.05504 0.05016 -0.0203 1.0000 0.1902
-5.000 -0.4730 0.03424 0.02682 -0.0148 1.0000 0.0820
-4.750 -0.4531 0.03146 0.02322 -0.0119 1.0000 0.0713
-4.500 -0.4336 0.02874 0.02024 -0.0104 1.0000 0.0696
-4.250 -0.4129 0.02698 0.01814 -0.0087 1.0000 0.0703
-4.000 -0.3909 0.02540 0.01625 -0.0072 1.0000 0.0710
-3.750 -0.3675 0.02373 0.01434 -0.0060 1.0000 0.0709
-3.500 -0.3434 0.02235 0.01277 -0.0049 1.0000 0.0715
-3.250 -0.3189 0.02087 0.01121 -0.0039 1.0000 0.0731
-3.000 -0.2955 0.01957 0.01002 -0.0031 1.0000 0.0768
-2.750 -0.2730 0.01883 0.00926 -0.0020 1.0000 0.0846
-2.500 -0.2511 0.01784 0.00842 -0.0010 1.0000 0.0956
-2.250 -0.0820 0.01364 0.00756 -0.0236 1.0000 1.0000
-2.000 -0.0779 0.01356 0.00734 -0.0200 1.0000 1.0000
-1.750 -0.0723 0.01357 0.00719 -0.0166 1.0000 1.0000
-1.500 -0.0652 0.01364 0.00712 -0.0134 1.0000 1.0000
-1.250 -0.0568 0.01377 0.00712 -0.0106 1.0000 1.0000
-1.000 -0.0475 0.01395 0.00719 -0.0079 1.0000 1.0000
-0.750 -0.0372 0.01419 0.00732 -0.0056 1.0000 1.0000
-0.500 0.0136 0.01445 0.00742 -0.0109 0.9906 1.0000
-0.250 0.0740 0.01462 0.00746 -0.0179 0.9775 1.0000
0.000 0.1346 0.01466 0.00741 -0.0247 0.9634 1.0000
0.250 0.1964 0.01455 0.00725 -0.0315 0.9486 1.0000
0.500 0.2558 0.01427 0.00696 -0.0374 0.9315 1.0000
0.750 0.3066 0.01388 0.00657 -0.0412 0.9100 1.0000
1.000 0.3454 0.01349 0.00616 -0.0424 0.8820 1.0000
1.250 0.3758 0.01316 0.00579 -0.0417 0.8469 1.0000
1.500 0.4036 0.01292 0.00544 -0.0404 0.8073 1.0000
1.750 0.4279 0.01286 0.00520 -0.0385 0.7603 1.0000
2.000 0.4507 0.01297 0.00509 -0.0366 0.7098 1.0000
2.250 0.4732 0.01321 0.00505 -0.0349 0.6605 1.0000
2.500 0.4957 0.01356 0.00511 -0.0334 0.6169 1.0000
2.750 0.5186 0.01396 0.00529 -0.0321 0.5795 1.0000
3.000 0.5418 0.01439 0.00552 -0.0311 0.5492 1.0000
3.250 0.5653 0.01484 0.00579 -0.0301 0.5237 1.0000
3.500 0.5890 0.01529 0.00610 -0.0293 0.5018 1.0000
3.750 0.6128 0.01575 0.00648 -0.0285 0.4819 1.0000
4.000 0.6366 0.01621 0.00688 -0.0277 0.4637 1.0000
4.250 0.6607 0.01670 0.00732 -0.0270 0.4475 1.0000
4.500 0.6846 0.01721 0.00779 -0.0262 0.4323 1.0000
4.750 0.7086 0.01775 0.00832 -0.0255 0.4181 1.0000
5.000 0.7327 0.01832 0.00889 -0.0248 0.4052 1.0000
5.250 0.7569 0.01892 0.00948 -0.0242 0.3933 1.0000
5.500 0.7812 0.01954 0.01006 -0.0236 0.3819 1.0000
5.750 0.8046 0.02014 0.01083 -0.0228 0.3704 1.0000
6.000 0.8282 0.02082 0.01161 -0.0221 0.3599 1.0000
6.250 0.8524 0.02151 0.01231 -0.0215 0.3503 1.0000
6.500 0.8757 0.02217 0.01310 -0.0207 0.3401 1.0000
6.750 0.8981 0.02280 0.01391 -0.0198 0.3287 1.0000
7.000 0.9205 0.02332 0.01452 -0.0189 0.3164 1.0000
7.250 0.9428 0.02377 0.01503 -0.0179 0.3039 1.0000
7.500 0.9647 0.02413 0.01545 -0.0169 0.2907 1.0000
7.750 0.9849 0.02425 0.01571 -0.0155 0.2747 1.0000
8.000 1.0041 0.02423 0.01581 -0.0141 0.2572 1.0000
8.250 1.0229 0.02419 0.01588 -0.0125 0.2396 1.0000
8.500 1.0398 0.02413 0.01593 -0.0107 0.2187 1.0000
8.750 1.0532 0.02411 0.01607 -0.0084 0.1863 1.0000
9.000 1.0599 0.02509 0.01684 -0.0055 0.1282 1.0000
9.250 1.0655 0.02715 0.01860 -0.0026 0.0947 1.0000
9.500 1.0730 0.02914 0.02050 0.0001 0.0799 1.0000
9.750 1.0813 0.03114 0.02250 0.0026 0.0705 1.0000
10.000 1.0912 0.03343 0.02464 0.0046 0.0640 1.0000
10.250 1.1050 0.03546 0.02691 0.0065 0.0593 1.0000
10.500 1.1176 0.03748 0.02896 0.0082 0.0547 1.0000
10.750 1.1329 0.04059 0.03216 0.0093 0.0514 1.0000
11.000 1.1436 0.04313 0.03505 0.0112 0.0497 1.0000
11.250 1.1509 0.04599 0.03825 0.0132 0.0484 1.0000
11.500 1.1536 0.04896 0.04154 0.0154 0.0474 1.0000
11.750 1.1505 0.05179 0.04464 0.0180 0.0465 1.0000
12.000 1.1449 0.05463 0.04771 0.0204 0.0456 1.0000
12.250 1.1381 0.05761 0.05089 0.0222 0.0447 1.0000
12.500 1.1271 0.06097 0.05446 0.0235 0.0442 1.0000
12.750 1.1129 0.06481 0.05853 0.0240 0.0438 1.0000
13.000 1.0932 0.06944 0.06341 0.0233 0.0439 1.0000
13.250 1.0504 0.07738 0.07180 0.0190 0.0458 1.0000
13.500 1.0106 0.08702 0.08174 0.0124 0.0477 1.0000
13.750 0.9763 0.09718 0.09206 0.0055 0.0493 1.0000
14.000 0.9449 0.10779 0.10276 -0.0014 0.0507 1.0000
14.250 0.9185 0.11802 0.11300 -0.0072 0.0517 1.0000
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Polar data table (+)
Polar graphs
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