RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 12A-1.8/9.0 AIRFOIL (rg12a189-il) Reynolds number: 100,000 Max Cl/Cd: 49.63 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg12a189-il-100000-n5.txt Download as CSV file: xf-rg12a189-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 12A-1.8/9.0 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4810 0.11310 0.10780 -0.0198 1.0000 0.0283
-10.250 -0.4785 0.10918 0.10391 -0.0205 1.0000 0.0267
-10.000 -0.4782 0.10498 0.09975 -0.0219 1.0000 0.0253
-9.500 -0.4886 0.09256 0.08746 -0.0293 1.0000 0.0212
-9.250 -0.4899 0.08869 0.08364 -0.0302 1.0000 0.0209
-9.000 -0.4924 0.08464 0.07965 -0.0316 1.0000 0.0206
-8.750 -0.4977 0.08005 0.07513 -0.0337 1.0000 0.0204
-8.500 -0.5041 0.07567 0.07082 -0.0361 1.0000 0.0201
-8.250 -0.5164 0.07108 0.06628 -0.0384 1.0000 0.0198
-8.000 -0.5259 0.06641 0.06159 -0.0398 1.0000 0.0196
-7.750 -0.5334 0.06182 0.05693 -0.0406 1.0000 0.0193
-7.500 -0.5382 0.05739 0.05239 -0.0407 1.0000 0.0190
-7.250 -0.5407 0.05290 0.04771 -0.0403 1.0000 0.0188
-7.000 -0.5402 0.04848 0.04304 -0.0395 1.0000 0.0186
-6.750 -0.5362 0.04426 0.03850 -0.0384 1.0000 0.0184
-6.500 -0.5291 0.04014 0.03399 -0.0371 1.0000 0.0183
-6.250 -0.5183 0.03643 0.02983 -0.0358 1.0000 0.0184
-6.000 -0.5040 0.03331 0.02623 -0.0345 1.0000 0.0191
-5.750 -0.4867 0.03060 0.02293 -0.0331 1.0000 0.0205
-5.500 -0.4674 0.02838 0.02020 -0.0317 1.0000 0.0213
-5.250 -0.4479 0.02579 0.01728 -0.0306 1.0000 0.0219
-5.000 -0.4272 0.02392 0.01520 -0.0295 1.0000 0.0228
-4.750 -0.4058 0.02243 0.01354 -0.0284 1.0000 0.0240
-4.500 -0.3840 0.02112 0.01208 -0.0273 1.0000 0.0257
-4.250 -0.3620 0.02009 0.01089 -0.0262 1.0000 0.0289
-4.000 -0.3406 0.01907 0.00981 -0.0253 1.0000 0.0338
-3.750 -0.3185 0.01820 0.00883 -0.0243 1.0000 0.0390
-3.500 -0.2962 0.01741 0.00801 -0.0235 1.0000 0.0514
-3.250 -0.2737 0.01655 0.00725 -0.0228 1.0000 0.0758
-3.000 -0.2379 0.01565 0.00678 -0.0251 0.9947 0.1540
-2.750 -0.2042 0.01466 0.00639 -0.0271 0.9885 0.2924
-2.500 -0.1717 0.01361 0.00621 -0.0286 0.9828 0.5020
-2.250 -0.1481 0.01321 0.00657 -0.0266 0.9741 0.7209
-2.000 -0.1195 0.01325 0.00661 -0.0259 0.9651 0.7949
-1.750 -0.0880 0.01328 0.00656 -0.0258 0.9570 0.8400
-1.500 -0.0598 0.01325 0.00646 -0.0251 0.9468 0.8744
-1.250 -0.0278 0.01322 0.00634 -0.0252 0.9376 0.9042
-1.000 0.0141 0.01318 0.00620 -0.0273 0.9312 0.9312
-0.750 0.0606 0.01315 0.00604 -0.0307 0.9236 0.9546
-0.500 0.1171 0.01309 0.00587 -0.0362 0.9185 0.9724
-0.250 0.1697 0.01299 0.00567 -0.0413 0.9103 0.9841
0.000 0.2197 0.01283 0.00544 -0.0458 0.9011 0.9906
0.250 0.2642 0.01267 0.00523 -0.0492 0.8884 0.9968
0.500 0.3021 0.01253 0.00504 -0.0513 0.8725 1.0000
0.750 0.3332 0.01240 0.00487 -0.0520 0.8536 1.0000
1.000 0.3655 0.01228 0.00471 -0.0528 0.8345 1.0000
1.250 0.3948 0.01221 0.00461 -0.0530 0.8134 1.0000
1.500 0.4234 0.01217 0.00451 -0.0530 0.7912 1.0000
1.750 0.4491 0.01218 0.00447 -0.0525 0.7676 1.0000
2.000 0.4745 0.01223 0.00446 -0.0519 0.7438 1.0000
2.250 0.4992 0.01231 0.00450 -0.0512 0.7197 1.0000
2.500 0.5227 0.01244 0.00457 -0.0502 0.6950 1.0000
2.750 0.5464 0.01260 0.00466 -0.0493 0.6700 1.0000
3.000 0.5702 0.01278 0.00478 -0.0484 0.6446 1.0000
3.250 0.5939 0.01299 0.00496 -0.0475 0.6186 1.0000
3.500 0.6175 0.01323 0.00514 -0.0465 0.5916 1.0000
3.750 0.6410 0.01349 0.00535 -0.0456 0.5639 1.0000
4.000 0.6644 0.01377 0.00558 -0.0447 0.5351 1.0000
4.250 0.6876 0.01408 0.00587 -0.0438 0.5052 1.0000
4.500 0.7105 0.01442 0.00616 -0.0428 0.4736 1.0000
4.750 0.7332 0.01480 0.00648 -0.0418 0.4409 1.0000
5.000 0.7554 0.01522 0.00683 -0.0408 0.4075 1.0000
5.250 0.7776 0.01567 0.00727 -0.0398 0.3721 1.0000
5.500 0.7991 0.01619 0.00770 -0.0388 0.3359 1.0000
5.750 0.8204 0.01675 0.00820 -0.0378 0.2978 1.0000
6.000 0.8414 0.01738 0.00875 -0.0368 0.2602 1.0000
6.250 0.8618 0.01809 0.00937 -0.0357 0.2220 1.0000
6.500 0.8810 0.01896 0.01005 -0.0346 0.1763 1.0000
6.750 0.8989 0.02002 0.01086 -0.0335 0.1274 1.0000
7.000 0.9176 0.02106 0.01176 -0.0324 0.0935 1.0000
7.250 0.9356 0.02221 0.01286 -0.0312 0.0700 1.0000
7.500 0.9517 0.02357 0.01413 -0.0297 0.0530 1.0000
7.750 0.9685 0.02482 0.01543 -0.0282 0.0429 1.0000
8.000 0.9838 0.02619 0.01693 -0.0265 0.0383 1.0000
8.250 0.9994 0.02755 0.01849 -0.0248 0.0350 1.0000
8.500 1.0141 0.02901 0.02007 -0.0232 0.0327 1.0000
8.750 1.0265 0.03092 0.02204 -0.0214 0.0309 1.0000
9.000 1.0429 0.03265 0.02397 -0.0200 0.0295 1.0000
9.250 1.0592 0.03428 0.02586 -0.0186 0.0272 1.0000
9.500 1.0737 0.03605 0.02784 -0.0172 0.0254 1.0000
9.750 1.0872 0.03814 0.03014 -0.0158 0.0244 1.0000
10.000 1.0987 0.04041 0.03262 -0.0143 0.0235 1.0000
10.250 1.1075 0.04302 0.03544 -0.0127 0.0228 1.0000
10.500 1.1116 0.04630 0.03896 -0.0108 0.0221 1.0000
10.750 1.1091 0.04908 0.04212 -0.0082 0.0216 1.0000
11.000 1.1028 0.05184 0.04524 -0.0056 0.0210 1.0000
11.250 1.0931 0.05493 0.04867 -0.0036 0.0205 1.0000
11.500 1.0807 0.05843 0.05247 -0.0024 0.0201 1.0000
11.750 1.0658 0.06250 0.05682 -0.0023 0.0198 1.0000
12.000 1.0490 0.06723 0.06181 -0.0033 0.0197 1.0000
12.250 1.0305 0.07275 0.06756 -0.0056 0.0198 1.0000
12.500 1.0103 0.07924 0.07426 -0.0092 0.0199 1.0000
12.750 0.9890 0.08678 0.08198 -0.0141 0.0202 1.0000
13.000 0.9668 0.09540 0.09070 -0.0199 0.0206 1.0000
13.250 0.9456 0.10474 0.10012 -0.0261 0.0211 1.0000
13.500 0.9259 0.11443 0.10986 -0.0322 0.0216 1.0000
13.750 0.9078 0.12444 0.11990 -0.0382 0.0219 1.0000
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Polar data table (+)
Polar graphs
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