RAE 104 AIRFOIL (rae104-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 104 AIRFOIL (rae104-il) Reynolds number: 200,000 Max Cl/Cd: 44.81 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae104-il-200000.txt Download as CSV file: xf-rae104-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 104 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5074 0.11311 0.10969 -0.0184 1.0000 0.0549
-11.500 -0.5207 0.10724 0.10385 -0.0228 1.0000 0.0553
-8.750 -0.7411 0.05980 0.05580 -0.0307 1.0000 0.0585
-8.500 -0.7394 0.05693 0.05286 -0.0289 1.0000 0.0599
-8.250 -0.7398 0.05405 0.04985 -0.0266 1.0000 0.0619
-8.000 -0.7416 0.05127 0.04683 -0.0237 1.0000 0.0650
-7.000 -0.7362 0.03103 0.02416 -0.0053 1.0000 0.0319
-6.750 -0.7246 0.02919 0.02198 -0.0024 1.0000 0.0321
-6.500 -0.7136 0.02511 0.01761 0.0001 1.0000 0.0339
-6.250 -0.6990 0.02364 0.01604 0.0023 1.0000 0.0356
-6.000 -0.6833 0.02219 0.01443 0.0046 1.0000 0.0367
-5.750 -0.6676 0.02095 0.01306 0.0069 1.0000 0.0382
-5.500 -0.6525 0.01990 0.01190 0.0092 1.0000 0.0402
-5.250 -0.6380 0.01940 0.01127 0.0116 1.0000 0.0429
-5.000 -0.6252 0.01792 0.00980 0.0141 1.0000 0.0471
-4.750 -0.6118 0.01723 0.00910 0.0165 1.0000 0.0512
-4.500 -0.5808 0.01619 0.00804 0.0153 0.9962 0.0597
-4.250 -0.5491 0.01530 0.00719 0.0140 0.9916 0.0750
-4.000 -0.5198 0.01422 0.00636 0.0130 0.9866 0.1198
-3.750 -0.5025 0.01213 0.00563 0.0134 0.9810 0.3754
-3.500 -0.4898 0.01093 0.00575 0.0163 0.9740 0.6540
-3.250 -0.4580 0.01103 0.00598 0.0160 0.9702 0.7336
-3.000 -0.4330 0.01116 0.00609 0.0170 0.9640 0.7716
-2.750 -0.4025 0.01133 0.00622 0.0170 0.9597 0.8005
-2.500 -0.3687 0.01155 0.00641 0.0163 0.9567 0.8244
-2.250 -0.3427 0.01173 0.00657 0.0172 0.9515 0.8436
-2.000 -0.3123 0.01198 0.00679 0.0174 0.9473 0.8612
-1.750 -0.2774 0.01226 0.00702 0.0166 0.9445 0.8772
-1.500 -0.2381 0.01253 0.00724 0.0148 0.9427 0.8900
-1.250 -0.2064 0.01271 0.00737 0.0143 0.9387 0.9007
-1.000 -0.1680 0.01291 0.00752 0.0123 0.9354 0.9077
-0.750 -0.1306 0.01296 0.00753 0.0102 0.9322 0.9145
-0.500 -0.0825 0.01306 0.00760 0.0059 0.9308 0.9172
-0.250 -0.0359 0.01310 0.00762 0.0019 0.9292 0.9203
0.000 0.0001 0.01308 0.00759 0.0000 0.9255 0.9255
0.250 0.0360 0.01310 0.00762 -0.0019 0.9203 0.9292
0.500 0.0824 0.01307 0.00761 -0.0059 0.9173 0.9308
0.750 0.1305 0.01296 0.00754 -0.0102 0.9145 0.9322
1.000 0.1681 0.01291 0.00752 -0.0123 0.9077 0.9354
1.250 0.2065 0.01270 0.00737 -0.0143 0.9007 0.9387
1.500 0.2382 0.01253 0.00724 -0.0149 0.8899 0.9427
1.750 0.2775 0.01225 0.00701 -0.0166 0.8771 0.9445
2.000 0.3124 0.01198 0.00679 -0.0173 0.8610 0.9473
2.250 0.3427 0.01174 0.00658 -0.0172 0.8439 0.9515
2.500 0.3687 0.01155 0.00641 -0.0163 0.8242 0.9567
2.750 0.4025 0.01133 0.00623 -0.0170 0.8007 0.9597
3.000 0.4330 0.01115 0.00609 -0.0170 0.7715 0.9640
3.250 0.4581 0.01103 0.00598 -0.0160 0.7339 0.9703
3.500 0.4898 0.01093 0.00575 -0.0163 0.6542 0.9740
4.000 0.5198 0.01422 0.00636 -0.0130 0.1201 0.9866
4.250 0.5491 0.01529 0.00719 -0.0140 0.0754 0.9916
4.500 0.5809 0.01618 0.00803 -0.0153 0.0599 0.9962
4.750 0.6118 0.01723 0.00909 -0.0165 0.0512 1.0000
5.000 0.6253 0.01792 0.00980 -0.0141 0.0473 1.0000
5.250 0.6380 0.01937 0.01124 -0.0116 0.0429 1.0000
5.500 0.6525 0.01990 0.01190 -0.0092 0.0402 1.0000
5.750 0.6676 0.02094 0.01306 -0.0069 0.0382 1.0000
6.000 0.6833 0.02218 0.01442 -0.0046 0.0367 1.0000
6.250 0.6991 0.02365 0.01605 -0.0023 0.0356 1.0000
6.500 0.7136 0.02511 0.01761 -0.0001 0.0339 1.0000
6.750 0.7247 0.02920 0.02199 0.0023 0.0321 1.0000
7.000 0.7362 0.03096 0.02409 0.0053 0.0318 1.0000
7.500 0.7158 0.02470 0.01941 0.0165 0.0385 1.0000
8.250 0.6877 0.04286 0.03895 0.0295 0.0649 1.0000
8.500 0.6780 0.04644 0.04272 0.0323 0.0628 1.0000
8.750 0.6667 0.05006 0.04648 0.0347 0.0612 1.0000
9.000 0.6503 0.05343 0.04993 0.0374 0.0605 1.0000
9.250 0.6280 0.05696 0.05354 0.0395 0.0602 1.0000
9.500 0.5996 0.06165 0.05829 0.0392 0.0604 1.0000
9.750 0.5677 0.06828 0.06499 0.0360 0.0609 1.0000
10.000 0.5400 0.07698 0.07368 0.0299 0.0613 1.0000
10.250 0.5277 0.08330 0.07997 0.0268 0.0604 1.0000
10.500 0.5220 0.08836 0.08501 0.0250 0.0592 1.0000
10.750 0.5223 0.09238 0.08902 0.0244 0.0580 1.0000
11.000 0.5501 0.09335 0.08999 0.0323 0.0555 1.0000
11.250 0.5325 0.10070 0.09735 0.0271 0.0555 1.0000
11.500 0.5200 0.10714 0.10374 0.0227 0.0553 1.0000
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Polar data table (+)
Polar graphs
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